CN113091526B - Automatic adjusting device for optimal attitude of warhead under any attack angle of missile - Google Patents
Automatic adjusting device for optimal attitude of warhead under any attack angle of missile Download PDFInfo
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- CN113091526B CN113091526B CN202110162483.5A CN202110162483A CN113091526B CN 113091526 B CN113091526 B CN 113091526B CN 202110162483 A CN202110162483 A CN 202110162483A CN 113091526 B CN113091526 B CN 113091526B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
Abstract
The invention discloses an automatic adjusting device for the optimal posture of a fighting part under any landing angle of a missile, wherein a posture adjusting support frame is provided with five rows of second round holes from top to bottom, the axis of each second round hole passes through the sphere center of the posture adjusting support frame, the inner side surface of each second round hole is a second concave circular ring surface, and one second round hole in the uppermost row of the posture adjusting support frame is positioned at the top of a second hollow spherical cavity; the liquid-phase loading warhead and the missile can rotate relatively, and for the missile with any attack angle, although the axis of the missile is not vertical to the ground, the warhead automatically adjusts to the posture that the axis is vertical to the ground under the action of gravity, and the posture is the optimal posture of the warhead. The axis of the cylindrical cloud cluster formed after the warhead is thrown is vertical to the ground. The coverage area of the cloud cluster on the ground target reaches the maximum, and the damage power of the liquid-phase charge warhead on the ground target can be best exerted.
Description
Technical Field
The invention belongs to the technical field of attitude adjustment, and relates to an automatic optimal attitude adjusting device, in particular to an automatic optimal attitude adjusting device for a warhead under any attack angle of a missile.
Background
The liquid-phase charging warhead is internally filled with high-energy fuel, the high-energy fuel is thrown into the air under the action of explosive explosion throwing driving, the high-energy fuel has an initial speed, then the high-energy fuel and the air perform convection motion, the high-energy fuel and the air are mixed to form a large-range active cloud cluster, and the active cloud cluster is detonated secondarily by the explosive to generate body detonation and release strong shock waves, so that the liquid-phase charging warhead is one of the most powerful non-nuclear weapons.
The field and garden et al report in the literature "numerical simulation study of the effect of cloud and mist morphology on detonation pressure field" (safety and environmental bulletin, 8 months in 2013, vol 13, page 182 of 4 th): the liquid-phase charging warhead forms a cylindrical active cloud cluster after being scattered, and the power of the active cloud cluster after secondary detonation is increased along with the increase of the coverage area.
The liquid-phase charging warhead is carried on a missile and launched, when the missile approaches an attack target, the axis of the missile is generally not perpendicular to the ground, and the speed direction is approximately perpendicular to the ground. Zhang Gong et al report in the document "guidance law with controllable missile impact angle in three-dimensional space" (flight mechanics, 2.2010, vol. 2, page 1, 65): the landing angle of the tail end of the missile is influenced by various factors, the axis of the missile forms a certain angle with the ground, and the speed direction can be adjusted to be approximately vertical to the ground.
The liquid-phase charging warhead is fixed on the missile, the axis of the liquid-phase charging warhead is coincident with the axis of the missile, the inner diameter of the missile is 435-555 mm, the diameter of the warhead is 380-395 mm, the weight of the warhead is 95-105 kg, the terminal speed of the missile and the warhead is 65-80 m/s, when the axis of the missile is not vertical to the ground, the axis of the liquid-phase charging warhead is not vertical to the ground, and the axis of a cylindrical cloud cluster formed after the liquid-phase charging warhead is thrown is not vertical to the ground. The liquid-phase powder-filled warhead is thrown after being inclined, the diameter of the fuel thrown obliquely downwards cannot be enlarged due to the fact that the fuel is blocked by the ground, the fuel thrown obliquely upwards flies to the sky and is far away from a ground target, the damage effect of subsequent explosion on the ground target is weakened, the vertical projection area of the inclined cloud cluster on the ground is reduced, the coverage area of the inclined cloud cluster on the ground target is reduced, and the damage effect of the liquid-phase powder-filled warhead on the ground target is reduced due to the above problems.
Disclosure of Invention
In order to overcome the defects and defects of the prior art, the invention provides the automatic adjusting device for the optimal posture of the warhead under any attack angle of the missile. The axis of the cylindrical cloud cluster formed after the warhead is thrown is vertical to the ground. The coverage area of the cloud cluster on the ground target reaches the maximum, and the damage power of the liquid-phase charge warhead on the ground target can be best exerted.
The invention provides an automatic adjusting device for the optimal attitude of a warhead under any attack angle of a missile, which comprises a missile shell 1, an attitude adjusting support frame 2, a ball 3 and a warhead 4;
the missile shell 1 is a revolving body, the missile shell 1 consists of a left part and a right part, the left part of the missile shell 1 is a first conical barrel, the right part of the missile shell 1 is a first barrel, and the first conical barrel and the first barrel of the missile shell 1 are connected at an opening;
the missile shell 1 is a missile shell carried by a liquid-phase loading warhead, and when the missile shell 1 approaches a target, the axis of the revolving body of the missile shell 1 and the ground can form any angle;
the posture adjusting support frame 2 is in the shape of a second hollow spherical cavity, the posture adjusting support frame 2 is provided with five rows of second round holes from top to bottom, the axis of each second round hole passes through the spherical center of the posture adjusting support frame 2, the inner side surface of each second round hole is a second concave circular ring surface, one second round hole is arranged in the topmost row of the posture adjusting support frame 2 and is positioned at the top of the second hollow spherical cavity, four second round holes are uniformly distributed along the circumferential direction and are positioned at forty-five degrees of north latitude of the second hollow spherical cavity, eight second round holes are arranged in the third row from top to bottom of the posture adjusting support frame 2 and are uniformly distributed along the circumferential direction and are positioned at the position of the equator of the second hollow spherical cavity, four second round holes are uniformly distributed along the circumferential direction and are positioned at the south forty-five degrees of the second hollow spherical cavity, one second round hole in the lowest row of the posture adjusting support frame 2 is positioned at the bottom of the second hollow sphere cavity;
the posture adjusting support frame 2 is positioned inside the first barrel body of the missile shell 1, the outer surface of the posture adjusting support frame 2 is welded and connected with the inner surface of the first barrel body of the missile shell 1 through a plurality of second steel frames, and the posture adjusting support frame 2 and the missile shell 1 cannot move relatively under the support and connection of the second steel frames;
the shape of the ball 3 is a third sphere, and the total number of the ball 3 is eighteen;
the ball 3 is positioned in a second round hole of the posture adjusting support frame 2, and the outer surface of the ball 3 is in free rotation fit contact with a second concave circular surface of the posture adjusting support frame 2;
the shape of the warhead 4 is a fourth sphere, and the centroid of the warhead 4 is right below the centroid of the fourth sphere;
the warhead 4 is positioned in the attitude adjusting support frame 2, the outer surface of the warhead 4 is in rolling fit contact with the outer surface of the ball 3, the warhead 4 is a liquid-phase explosive-filled warhead, the warhead 4 carries a missile for launching, the internal diameter of the missile is 435-555 mm, the diameter of the warhead of the liquid-phase explosive-filled warhead is 380-395 mm, the weight of the warhead is 95-105 kg, the terminal speed of the missile and the warhead is 65-80 m/s, the interior of the warhead 4 is provided with explosive throwing, the explosive throwing inside the warhead 4 is a cylinder, a cloud cluster formed after the warhead 4 throws is cylindrical, the axis of the explosive throwing inside the warhead 4 is coincident with the axis of the cylinder of the cloud cluster after throwing, although the axis of the missile is not perpendicular to the ground, and the optimal attitude automatic adjusting device of the warhead under any attack angle of the missile is used for adjusting the axis of the explosive throwing inside the warhead 4 to be perpendicular to the ground, so that the axis of the cylinder of the cloud cluster after throwing 4 is perpendicular to the ground;
the ratio of the distance of the centroid of the warhead 4 located right below the centroid of the fourth sphere to the diameter of the fourth sphere is 1: 6.1 to 6.4;
the clearance between the outer surface of the ball 3 and the second concave circular ring surface of the posture adjusting support frame 2 is 0.09-0.26 mm;
the clearance between the outer surface of the warhead 4 and the outer surface of the ball 3 is 0.44-0.75 mm;
the use method of the automatic adjusting device for the optimal attitude of the warhead of the missile under any attack angle comprises the following steps:
step 1: assembling the warhead 4 and the attitude adjusting support frame 2;
step 2: assembling the ball 3 with the posture adjusting support frame 2;
and step 3: assembling the attitude adjusting support frame 2 with the missile shell 1;
and 4, step 4: when the axis of the revolving body of the missile shell 1 is not perpendicular to the ground, the external force disturbs the warhead 4, the axis of the warhead 4 deflects, the gravity center of the warhead 4 deviates from the lowest end of the centroid of the warhead 4, the gravity of the warhead 4 generates reverse torque on the warhead 4, the warhead 4 reversely rotates under the torque, until the gravity center of the warhead 4 is just at the lowest end of the centroid of the warhead 4, the gravity of the warhead 4 cannot generate torque on the warhead 4, the warhead 4 is in a stable state, and the attitude of the warhead 4 is balanced, so that the explosive thrown inside the warhead 4 can be adjusted to be perpendicular to the ground under the gravity effect of the warhead 4, and the cloud cluster axis formed after the explosive thrown inside the warhead 4 is perpendicular to the ground, covers and damages a ground target.
Regarding the ratio of the distance of the centroid of the warhead 4 directly below the centroid of the fourth sphere to the diameter of the fourth sphere, the gap between the outer surface of the ball 3 and the second concave circular ring surface of the posture adjustment support frame 2, and the gap between the outer surface of the warhead 4 and the outer surface of the ball 3, any one of the following 2 modes can be adopted:
implementation mode 1: the ratio of the distance of the centroid of the warhead 4 under the centroid of the fourth sphere to the diameter of the fourth sphere is 1: 6.1;
the clearance between the outer surface of the ball 3 and the second concave circular ring surface of the posture adjusting support frame 2 is 0.09 mm;
the clearance between the outer surface of the warhead 4 and the outer surface of the ball 3 is 0.44 mm.
Implementation mode 2: the ratio of the distance of the centroid of the warhead 4 located right below the centroid of the fourth sphere to the diameter of the fourth sphere is 1: 6.4;
the range between the outer surface of the ball 3 and the second concave circular ring surface of the posture adjusting support frame 2 is 0.26 mm;
the clearance between the outer surface of the warhead 4 and the outer surface of the ball 3 is 0.75 mm.
The invention relates to an automatic adjusting device for the optimal attitude of the warhead of a missile under any attack angle, which brings the following technical effects:
the liquid-phase-charging missile disclosed by the invention is suitable for a missile with the inner diameter of 435-555 mm, the diameter of a liquid-phase-charging warhead part of 380-395 mm, the weight of the warhead part of 95-105 kg and the terminal speed of the missile and the warhead of 65-80 m/s. The axis of the cylindrical cloud cluster formed after the warhead is thrown is vertical to the ground. The coverage area of the cloud cluster on the ground target reaches the maximum, and the damage power of the liquid-phase charge warhead on the ground target can be best exerted.
Drawings
Fig. 1 is a schematic structural view of an automatic adjusting device for the optimal attitude of a warhead of a missile at any attack angle. 1. Missile casing, 2, attitude adjustment support frame, 3, ball, 4, warhead.
Detailed Description
The present invention is further described in detail with reference to the drawings and examples, it should be noted that the present invention is not limited to the following examples, and equivalent modifications based on the technical scheme of the present invention are within the scope of the present invention.
Example 1:
as shown in fig. 1, the present embodiment provides an automatic adjusting device for an optimal attitude of a warhead of a missile at any attack angle, which comprises a missile casing 1, an attitude adjusting support frame 2, balls 3 and a warhead 4;
the missile shell 1 is a revolving body, the missile shell 1 consists of a left part and a right part, the left part of the missile shell 1 is a first conical barrel, the right part of the missile shell 1 is a first barrel, and the first conical barrel and the first barrel of the missile shell 1 are connected at an opening;
the missile shell 1 is a missile shell carried by a liquid-phase loading warhead, and when the missile shell 1 approaches a target, the axis of the revolving body of the missile shell 1 and the ground can form any angle;
the posture adjusting support frame 2 is shaped as a second hollow spherical cavity, the posture adjusting support frame 2 is provided with five rows of second round holes from top to bottom, the axis of each second round hole passes through the spherical center of the posture adjusting support frame 2, the inner side surface of each second round hole is a second concave circular ring surface, the topmost row of second round holes of the posture adjusting support frame 2 is one, the four second round holes are positioned at the top of the second hollow spherical cavity, the four second round holes from top to bottom of the posture adjusting support frame 2 are uniformly distributed along the circumferential direction and are positioned at forty-five degrees of north latitude of the second hollow spherical cavity, the eight second round holes from top to bottom of the third row of second round holes of the posture adjusting support frame 2 are uniformly distributed along the circumferential direction and are positioned at the position of the equator of the second hollow spherical cavity, the four second round holes from top to bottom of the posture adjusting support frame 2 are uniformly distributed along the circumferential direction and are positioned at forty-five degrees of south latitude of the second hollow spherical cavity, one second round hole in the lowest row of the posture adjusting support frame 2 is positioned at the bottom of the second hollow sphere cavity;
the posture adjusting support frame 2 is positioned inside the first barrel body of the missile shell 1, the outer surface of the posture adjusting support frame 2 is welded and connected with the inner surface of the first barrel body of the missile shell 1 through a plurality of second steel frames, and the posture adjusting support frame 2 and the missile shell 1 cannot move relatively under the support and connection of the second steel frames;
the shape of the ball 3 is a third sphere, and the total number of the ball 3 is eighteen;
the ball 3 is positioned in a second round hole of the posture adjusting support frame 2, and the outer surface of the ball 3 is in free rotating fit contact with a second concave circular ring surface of the posture adjusting support frame 2;
the shape of the warhead 4 is a fourth sphere, and the centroid of the warhead 4 is right below the centroid of the fourth sphere;
the warhead 4 is positioned inside the attitude adjusting support frame 2, the outer surface of the warhead 4 is in rolling fit contact with the outer surface of the ball 3, the warhead 4 is a liquid-phase explosive-filled warhead, the warhead 4 carries a missile for launching, the inner diameter of the missile is 435-555 mm, the diameter of the warhead of the liquid-phase explosive-filled warhead is 380-395 mm, the weight of the warhead is 95-105 kg, the terminal speed of the missile and the warhead is 65-80 m/s, the inner part of the warhead 4 is provided with thrown explosives, the thrown explosives inside the warhead 4 is a cylinder, a cloud cluster formed after the warhead 4 is thrown is a cylinder, the axis of the thrown explosives inside the warhead 4 is coincident with the axis of the thrown cloud cluster cylinder, and although the axis of the missile is not perpendicular to the ground, the optimal attitude automatic adjusting device of the warhead under any attack angle of the missile is used for adjusting the axis of the thrown explosives inside the warhead 4 to be perpendicular to the ground, so that the axis of the thrown cloud cluster cylinder after the warhead 4 is thrown to be perpendicular to the ground;
the using method and the working principle of the invention are as follows:
the use method of the automatic adjusting device for the optimal attitude of the warhead of the missile under any attack angle comprises the following steps:
step 1: assembling the warhead 4 and the attitude adjusting support frame 2;
step 2: assembling the ball 3 with the posture adjusting support frame 2;
and step 3: assembling the attitude adjusting support frame 2 with the missile shell 1;
and 4, step 4: when the axis of the revolving body of the missile shell 1 is not perpendicular to the ground, the external force disturbs the warhead 4, the axis of the warhead 4 deflects, the gravity center of the warhead 4 deviates from the lowest end of the centroid of the warhead 4, the gravity of the warhead 4 generates reverse torque on the warhead 4, the warhead 4 reversely rotates under the torque, until the gravity center of the warhead 4 is just at the lowest end of the centroid of the warhead 4, the gravity of the warhead 4 cannot generate torque on the warhead 4, the warhead 4 is in a stable state, and the attitude of the warhead 4 is balanced, so that the explosive thrown inside the warhead 4 can be adjusted to be perpendicular to the ground under the gravity effect of the warhead 4, and the cloud cluster axis formed after the explosive thrown inside the warhead 4 is perpendicular to the ground, covers and damages a ground target.
The working principle of the invention is as follows:
in the original scheme, the warhead 4 and the missile shell 1 are mechanically connected into a whole, and the missile shell 1 inevitably rotates in posture under the combined action of air resistance, gravity and initial speed, so that the warhead 4 inevitably rotates, and the rotated warhead 4 has poor posture, so that the cloud cluster after being thrown has poor posture and poor power.
Therefore, the main inventive work of the invention is to change the fixed mechanical connection between the warhead 4 and the missile shell 1 into the freely and relatively rotatable rotation fit connection, and then solve the problems encountered by the new connection mode through the optimization of parameters and realize the lean refinement.
After the warhead 4 and the missile shell 1 can freely rotate relatively, although the missile shell 1 can rotate at any angle, the gravity center of the warhead 4 is positioned at the lower end of the centroid of the warhead 4, even if the warhead 4 is interfered, the rotation occurs, the warhead 4 has an automatic posture recovery function, because the warhead 4 can be stabilized only when the gravity center of the warhead 4 is positioned at the lowest end under the action of gravity and air resistance, other positions cannot be stabilized, the warhead 4 is equivalent to a tumbler, only the posture with the gravity center at the lowest end is a stable posture, and the rest postures are unstable. Certainly, the warhead 4 is much more complicated than a tumbler, the missile shell 1 is arranged outside the warhead 4, and the missile shell 1 still needs to move, so that the warhead 4 also needs to solve more complicated problems.
The missile shell 1 and the attitude adjusting support frame 2 are relatively fixed through mechanical connection. A large number of balls 3 are embedded on the posture adjusting support frame 2, and the balls 3 and the posture adjusting support frame 2 can freely rotate relatively. The ball 3 is located outside the fighting part 4, the ball 3 wraps the fighting part 4, and since the ball 3 can rotate freely, when the fighting part 4 needs to rotate, the ball 3 cannot obstruct the fighting part 4, so the external environment of the fighting part 4 has no obstacle to the rotation of the fighting part 4, the internal environment of the fighting part 4 is the combined action of gravity and air resistance, and since the gravity and the air resistance are both close to being perpendicular to the ground, the axis of the fighting part 4 can be relatively stable only when being perpendicular to the ground, if the axis of the fighting part 4 is not perpendicular to the ground, the combined force of the gravity and the air resistance will generate torque to the fighting part 4, the fighting part 4 will rotate, and until the axis of the fighting part 4 is perpendicular to the ground, the combined force of the gravity and the air resistance will not generate torque at the mass center of the fighting part 4, and the fighting part 4 will not rotate, is a relatively balanced state. Therefore, the attitude automatic recovery work of the warhead 4 can be smoothly completed.
When the ratio of the distance of the centroid of the fighting part 4 located right below the centroid of the fourth sphere to the diameter of the fourth sphere is too small, the distance of the centroid of the fighting part 4 located right below the centroid of the fourth sphere is too small, when the posture of the fighting part 4 rotates, the force arm of the gravity of the fighting part 4 is too small, the torque generated by the fighting part 4 under the action of the gravity is too small, the capacity of the fighting part 4 rotating to enable the posture of the fighting part to be perpendicular to the ground is too poor, the efficiency is too low, friction exists outside the fighting part 4, once the torque generated by the rotation of the fighting part 4 is lower than the torque generated by the friction, the fighting part 4 cannot rotate reversely, and the anti-collision device is invalid. When the ratio of the distance of the centroid of the fighting part 4 located right below the centroid of the fourth sphere to the diameter of the fourth sphere is too large, the distance of the centroid of the fighting part 4 located right below the centroid of the fourth sphere is too large, so-called adjusting the centroid of the fighting part 4 increases the counter weight at the lower end of the fighting part 4, the upper end of the fighting part 4 is provided with a cavity, the two occupy the inner space of the fighting part 4, and the beneficial effect is not generated on explosion, and the fighting part is stiff. Therefore, the stiffness of 4 is too large. In addition, the force arm of the gravity of the warhead 4 is too large, the torque generated by the warhead 4 under the action of the gravity is too large, the capability of rotating the warhead 4 to enable the posture of the warhead to be perpendicular to the ground is too sensitive, so that even if the warhead 4 rotates slightly and slightly, the gravity can also generate larger torque on the warhead 4 to enable the warhead 4 to rotate, slight interference can be caused, the repeated rotation motion of the warhead 4 can be caused, the warhead is equivalent to a pendulum of a pendulum clock and can swing back and forth all the time, and the subsequent explosive work is not facilitated, therefore, after the interference occurs, the warhead 4 can return to the optimal posture as soon as possible, and then the warhead can be kept stable, and the required result is also obtained; through a large number of experiments, the ratio of the distance of the centroid of the warhead 4 right below the centroid of the fourth sphere to the diameter of the fourth sphere is 1: 6.1-6.4, the above problems can be avoided, the above functions can be realized, and the use requirements can be met.
In this embodiment, the ratio of the distance between the centroid of the warhead 4 located right below the centroid of the fourth sphere and the diameter of the fourth sphere is 1: 6.1;
when the clearance between the outer surface of the ball 3 and the second concave circular ring surface of the posture adjustment support frame 2 is too small, the ball 3 rotates every time, the contact point between the ball 3 and the posture adjustment support frame 2 is too many, and the rotation of the ball 3 is restrained too much by the posture adjustment support frame 2. The friction force applied to the rotation of the balls 3 is too large to facilitate the free rotation of the balls 3, so that the effective adjustment of the posture of the fighting part 4 by the free rotation of the balls 3 is not facilitated; when the clearance between the outer surface of the ball 3 and the second concave circular ring surface of the posture adjustment support frame 2 is too large, the ball 3 is easily separated from the second circular hole of the posture adjustment support frame 2. In fact, the ball 3 is clamped in the second circular hole of the ball 2, so that the ball can rotate freely without being separated. Once the ball 3 is disengaged, the ball 3 cannot support the warhead 4, and the invention is disabled; a large number of experiments find that when the gap between the outer surface of the ball 3 and the second concave circular ring surface of the posture adjusting support frame 2 is 0.09-0.26 mm, the problems can be avoided, the functions can be realized, and the use requirement is met.
In this embodiment, the clearance between the outer surface of the ball 3 and the second concave circular ring surface of the posture adjustment support frame 2 is 0.09 mm;
when the clearance between the outer surface of the warhead 4 and the outer surface of the ball 3 is too small, the friction force of the ball 3 is too large when the warhead 4 rotates, which is not beneficial to the free rotation of the warhead 4, and the friction resistance of the free rotation of the warhead 4 is too large, which has influence on the free adjustment of the posture of the warhead 4; when the clearance between the surface of warhead 4 and the surface of ball 3 is too big, the activity space of warhead 4 is too big, warhead 4 can be in the inside beat of the ball face that a plurality of balls 3 enclose, when missile casing 1 flies promptly, the restraint that warhead 4 received is too little, and the space is too big, warhead 4 can freely beat in missile casing 1 is inside, the beat of warhead 4 causes the influence to the flight of missile casing 1, make 1 ballistic instability of missile casing, receive the influence, strike the accuracy reduction to the target. A large number of experiments find that when the clearance between the outer surface of the warhead 4 and the outer surface of the ball 3 is 0.44-0.75 mm, the problems can be avoided, the functions can be realized, and the use requirements are met.
In the present embodiment, the clearance between the outer surface of the warhead 4 and the outer surface of the ball 3 is 0.44 mm;
the invention is processed by 5 pieces, the attitude detector is arranged in the warhead 4, the axial deflection angle of the warhead 4 can be tried to be detected, then external force is applied to the missile shell 1 to enable the missile shell to rotate, twenty minutes later, the attitude detector in the warhead 4 is taken out, the result is read, the axial of the warhead 4 is perpendicular to the ground to serve as the optimal attitude, the maximum included angle between the axial of the warhead 4 and the optimal attitude is found to be 6 degrees, the range is an acceptable range, and damage to the target after the warhead 4 explodes is considered to have no influence. The invention is proved to be effective and feasible.
The invention relates to an automatic adjusting device for the optimal attitude of a warhead under any attack angle of a missile, which brings the following technical effects:
the liquid-phase-charging missile disclosed by the invention is suitable for a missile with the inner diameter of 435-555 mm, the diameter of a liquid-phase-charging warhead part of 380-395 mm, the weight of the warhead part of 95-105 kg and the terminal speed of the missile and the warhead of 65-80 m/s. The axis of the cylindrical cloud cluster formed after the warhead is thrown is vertical to the ground. The coverage area of the cloud cluster on the ground target reaches the maximum, and the damage power of the liquid-phase charge warhead on the ground target can be best exerted.
Example 2:
example 2 differs from example 1 in that:
in this embodiment, the ratio of the distance between the centroid of the warhead 4 located right below the centroid of the fourth sphere and the diameter of the fourth sphere is 1: 6.4;
in this embodiment, the gap between the outer surface of the ball 3 and the second concave circular ring surface of the attitude adjustment support frame 2 is 0.26 mm;
in this embodiment, the clearance between the outer surface of the warhead 4 and the outer surface of the ball 3 is 0.75 mm;
the invention is processed by 5 pieces, the attitude detector is arranged in the warhead 4, the axial deflection angle of the warhead 4 can be tried to be detected, then external force is applied to the missile shell 1 to enable the missile shell to rotate, twenty minutes later, the attitude detector in the warhead 4 is taken out, the result is read, the axial of the warhead 4 is perpendicular to the ground to serve as the optimal attitude, the maximum included angle between the axial of the warhead 4 and the optimal attitude is found to be 4 degrees, the range is an acceptable range, and damage to the target after the warhead 4 explodes is considered to have no influence. The invention is proved to be effective and feasible.
The invention relates to an automatic adjusting device for the optimal attitude of the warhead of a missile under any attack angle, which brings the following technical effects:
the liquid-phase-charging missile disclosed by the invention is suitable for a missile with the inner diameter of 435-555 mm, the diameter of a liquid-phase-charging warhead part of 380-395 mm, the weight of the warhead part of 95-105 kg and the terminal speed of the missile and the warhead of 65-80 m/s. The axis of the cylindrical cloud cluster formed after the warhead is thrown is vertical to the ground. The coverage area of the cloud cluster on the ground target reaches the maximum, and the damage power of the liquid-phase charge warhead on the ground target can be best exerted.
Claims (3)
1. An automatic adjusting device for the optimal attitude of a warhead of a guided missile at any attack angle comprises a guided missile shell (1), and is characterized by further comprising an attitude adjusting support frame (2), balls (3) and a warhead (4);
the missile shell (1) is a revolving body, the missile shell (1) consists of a left part and a right part, the left part of the missile shell (1) is a first conical barrel, the right part of the missile shell (1) is a first barrel, and the first conical barrel and the first barrel of the missile shell (1) are connected at an opening;
the missile shell (1) is a missile shell carried by a liquid-phase loading warhead, and when the missile shell (1) approaches a target, the axis of the revolving body of the missile shell (1) forms any angle with the ground;
the posture adjusting support frame (2) is in a second hollow spherical cavity, five rows of second round holes are formed in the posture adjusting support frame (2) from top to bottom, the axis of each second round hole passes through the spherical center of the posture adjusting support frame (2), the inner side surface of each second round hole is a second concave circular ring surface, one second round hole is arranged in the topmost row of the posture adjusting support frame (2) and is positioned at the top of the second hollow spherical cavity, four second round holes are arranged in the posture adjusting support frame (2) from top to bottom and are uniformly distributed along the circumferential direction, forty-five degrees are arranged in the north latitude of the second hollow spherical cavity, eight second round holes are arranged in the posture adjusting support frame (2) from top to bottom and are uniformly distributed along the circumferential direction and are positioned at the equator position of the second hollow spherical cavity, four round holes are arranged in the fourth row of the posture adjusting support frame (2) from top to bottom and are uniformly distributed along the circumferential direction, one second round hole is arranged in the lowermost row of the second hollow spherical cavity at forty-five degrees south latitude and is positioned at the bottom of the second hollow spherical cavity;
the posture adjusting support frame (2) is located inside a first barrel body of the missile shell (1), the outer surface of the posture adjusting support frame (2) is connected with the inner surface of the first barrel body of the missile shell (1) through a plurality of second steel frames in a welding mode, and the posture adjusting support frame (2) and the missile shell (1) cannot move relatively under the support connection of the second steel frames;
the shape of the balls (3) is a third sphere, and the total number of the balls (3) is eighteen;
the ball (3) is positioned in a second round hole of the posture adjusting support frame (2), and the outer surface of the ball (3) is in free rotating fit contact with a second concave circular surface of the posture adjusting support frame (2);
the shape of the fighting part (4) is a fourth sphere, and the centroid of the fighting part (4) is right below the centroid of the fourth sphere;
the warhead (4) is positioned inside the attitude adjusting support frame (2), the outer surface of the warhead (4) is in rolling fit contact with the outer surface of the ball (3), the warhead (4) is a liquid-phase charge warhead, the warhead (4) carries missiles to be launched, the inner diameters of the missiles are 435-555 mm, the diameters of the liquid-phase charge warheads are 380-395 mm, the weight of the warhead is 95-105 kg, the terminal speed of the missiles and the warhead is 65-80 m/s, the warhead (4) is internally provided with scattered explosives, the scattered explosives inside the warhead (4) are cylinders, a cloud cluster formed after the warhead (4) is scattered is cylindrical, the axis of the scattered explosives inside the warhead (4) is coincident with the axis of the dispersed cloud cluster cylinders, although the axis of the missiles is not perpendicular to the ground, the optimal attitude automatic adjusting device of the warhead under any landing angle is used for adjusting the axis of the scattered explosives inside the warhead (4) to be perpendicular to the ground, so that the axis of the cloud cluster cylinder after the warhead (4) is thrown is vertical to the ground;
the ratio of the distance of the centroid of the warhead (4) right below the centroid of the fourth sphere to the diameter of the fourth sphere is 1: 6.1-6.4;
the clearance between the outer surface of the ball (3) and the second concave circular ring surface of the posture adjusting support frame (2) is 0.09-0.26 mm;
the clearance between the outer surface of the warhead (4) and the outer surface of the ball (3) is 0.44-0.75 mm;
the use method of the automatic adjusting device for the optimal attitude of the warhead of the missile under any attack angle comprises the following steps:
step 1: assembling the warhead (4) and the attitude adjusting support frame (2);
step 2: assembling the ball (3) and the posture adjusting support frame (2);
and step 3: assembling the attitude adjusting support frame (2) with the missile shell (1);
and 4, step 4: when the axis of the revolving body of the missile shell (1) is not perpendicular to the ground, the external force disturbs the warhead (4), the axis of the warhead (4) deflects, the gravity center of the warhead (4) deviates from the lowest end of the centroid of the warhead (4), the gravity of the warhead (4) generates reverse torque to the warhead (4), the warhead (4) rotates reversely under the torque action until the gravity center of the warhead (4) is just at the lowest end of the centroid of the warhead (4), the gravity of the warhead (4) cannot generate torque to the warhead (4), the warhead (4) is in a stable state, the posture of the warhead (4) is balanced, therefore, the internal explosive throwing of the warhead (4) under the gravity action of the warhead (4) can be adjusted to be perpendicular to the ground, and the axis of a cloud formed after the internal explosive throwing of the warhead (4) is perpendicular to the ground, covering and damaging the ground target.
2. The automatic adjusting device for the optimal attitude of the warhead of a missile at any attack angle as claimed in claim 1, wherein the ratio of the distance of the centroid of the warhead (4) right below the centroid of the fourth sphere to the diameter of the fourth sphere is 1: 6.1;
the clearance between the outer surface of the ball (3) and the second concave circular ring surface of the posture adjusting support frame (2) is 0.09 mm;
the clearance between the outer surface of the warhead (4) and the outer surface of the ball (3) is 0.44 mm.
3. The automatic adjusting device for the optimal attitude of the warhead of a missile at any attack angle as claimed in claim 1, wherein the ratio of the distance of the centroid of the warhead (4) right below the centroid of the fourth sphere to the diameter of the fourth sphere is 1: 6.4;
the range between the outer surface of the ball (3) and the second concave circular ring surface of the posture adjusting support frame (2) is 0.26 mm;
the clearance between the outer surface of the warhead (4) and the outer surface of the ball (3) is 0.75 mm.
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| CN115285080A (en) * | 2022-08-04 | 2022-11-04 | 西安近代化学研究所 | Support arrangement for shift warhead gravity to ground |
| CN115284998B (en) * | 2022-08-04 | 2023-06-09 | 西安近代化学研究所 | Vehicle-mounted lifting device suitable for ten-ton warhead |
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| GB2126319B (en) * | 1982-08-31 | 1986-07-02 | Sven Landstrom | Device for underwater missiles for use against submerged submarines |
| US4493262A (en) * | 1982-11-03 | 1985-01-15 | The United States Of America As Represented By The Secretary Of The Navy | Fuel air explosive device |
| US6012393A (en) * | 1995-08-17 | 2000-01-11 | State Of Israel-Ministry Of Defense, Rafael-Armamient Dieve | Asymmetric penetration warhead |
| US7137588B2 (en) * | 2004-01-06 | 2006-11-21 | United Technologies Corporation | Ballistic target defense system and methods |
| US20120186482A1 (en) * | 2010-04-02 | 2012-07-26 | Lloyd Richard M | Kinetic energy rod warhead with blast fragmentation |
| CN103105103B (en) * | 2012-12-21 | 2015-03-11 | 哈尔滨工业大学 | Ammunition with head capable of deflecting and based on smart material driver |
| CN106482588B (en) * | 2016-11-28 | 2018-09-07 | 湖北航天飞行器研究所 | A kind of device for circumferential adjustment fragment emission direction |
| CN106938595B (en) * | 2017-03-09 | 2019-01-29 | 西安交通大学 | A kind of amphibious sandy beach spherical shape tour bus of servo motor bias direct-drive type |
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