阅读说明：本技术 一种飞行器一体化巡飞弹的工作方法 (Working method of integrated flying patrol of aircraft ) 是由 顾文彬 王震 何雷 毛益明 陆鸣 谢兴博 钟明寿 胡云昊 陈裕田 韩阳明 符磊 于 2019-07-30 设计创作，主要内容包括：本发明涉及一种飞行器一体化巡飞弹的工作方法,包括：多种中不同模式切换,具有对空中目标快速追踪攻击和地面目标悬停打击的能力。本发明提供的飞行器一体化巡飞弹的工作方法,综合集成了巡航探测、追踪攻击、悬停打击等多种功能。(The invention relates to a working method of an integrated flying patrol bomb of an aircraft, which comprises the following steps: the multi-mode switch has the capability of quickly tracking and attacking the aerial target and hovering and striking the ground target. The working method of the integrated patrol missile of the aircraft provided by the invention integrates various functions of cruise detection, attack tracking, hovering striking and the like.)

1. The working method of the integrated flying patrol bomb of the aircraft is characterized by comprising the following steps of: a bullet, a bullet body and a bullet tail; the warhead comprises a housing and a camera and a shaped jet warhead disposed within the housing; the projectile body is provided with wings and a projectile body rotor wing; the bullet tail is provided with an energy-gathering EFP warhead part, an empennage and a tail rotor wing; the wings can be unfolded and retracted, and when the wings are unfolded, the wings are perpendicular to the projectile body; when the span is retracted, the wing is parallel to the projectile body; the tail wing can be unfolded and folded, and when the wing is unfolded, the tail wing is perpendicular to the missile tail; when the span is retracted, the tail extends rearward of the tail and parallel to the projectile tail; the projectile body rotor wing is connected with the projectile body through a first connecting rod; the first connecting rod can be unfolded and retracted; when the first connecting rod is unfolded, the first connecting rod is perpendicular to the projectile body; when the first connecting rod is retracted, the first connecting rod is accommodated in the elastic body and can rotate by taking the axis of the first connecting rod as an axis; a first vector control mechanism is arranged between the projectile body rotor wing and the first connecting rod; the first vector control mechanism comprises a first bracket hinged with the first connecting rod and a second bracket hinged with the first bracket; the hinge shafts of the first bracket and the second bracket are vertical to each other, and the hinge shaft of the first bracket is also vertical to the axis of the first connecting rod; the second bracket is provided with a first driving shaft for driving the elastomer rotor, the elastomer rotor is hinged on the first driving shaft and can move between positions parallel and vertical to the axis of the first connecting rod; the tail rotor wing is connected with the missile tail through a second connecting rod; the second connecting rod can be unfolded and retracted; when the second connecting rod is unfolded, the second connecting rod is vertical to the bullet tail; when the second connecting rod is retracted, the second connecting rod extends towards the rear part of the bullet tail; a second vector control mechanism is arranged between the tail rotor and the second connecting rod; the second vector control mechanism comprises a third bracket hinged with the second connecting rod and a fourth bracket hinged with the third bracket; the hinge shafts of the third bracket and the fourth bracket are vertical to each other, and the hinge shaft of the third bracket is also vertical to the axis of the second connecting rod; the fourth bracket is provided with a second driving shaft for driving the tail rotor, the tail rotor is hinged on the second driving shaft, and the tail rotor can move between positions parallel and vertical to the axis of the second connecting rod;

the integrated flying patrol bomb of the aircraft can be switched among a full-folding mode, a front flying mode and a hovering mode; when the integrated patrol missile of the aircraft is in a fully-folded mode, the wings are retracted and are in a position parallel to the missile body; the first connecting rod retracts to be accommodated in the projectile body, and the projectile body rotor wing retracts to be in a position parallel to the axis of the first connecting rod; the second connecting rod is retracted to a position extending towards the rear of the projectile tail; the tail rotor wing is retracted and is in a position parallel to the axis of the second connecting rod;

when the integrated patrol missile of the aircraft is in a forward flight mode, the wings are unfolded and are in a position vertical to the missile body; the first connecting rod is unfolded and is positioned at a position vertical to the projectile body, and the projectile body rotor wing is unfolded and is positioned at a position vertical to the axis of the first connecting rod; the second connecting rod is unfolded and is in a position vertical to the bullet tail; the tail rotor is unfolded and is in a position perpendicular to the axis of the second connecting rod; the first connecting rod and the first vector control mechanism drive the projectile rotor wing to face forwards, and the second vector control mechanism drives the tail rotor wing to face backwards;

when the integrated cruise missile of the aircraft is in a hovering mode, the wings are unfolded and are in a position vertical to the missile body; the first connecting rod is unfolded and is positioned at a position vertical to the projectile body, and the projectile body rotor wing is unfolded and is positioned at a position vertical to the axis of the first connecting rod; the second connecting rod is unfolded and is in a position vertical to the bullet tail; the tail rotor is unfolded and is in a position perpendicular to the axis of the second connecting rod; the first connecting rod and the first vector control mechanism drive the projectile rotor to face upwards, and the second vector control mechanism drives the tail rotor to face upwards.

2. The working method of the integrated patrol missile of the aircraft according to claim 1, characterized in that: the integrated flying patrol of the aircraft is of a cylindrical structure with the caliber of 180mm and the length of 1200 mm.

3. The working method of the integrated patrol missile of the aircraft according to claim 1, characterized in that: the wing span is 1600 mm.

4. The working method of the integrated patrol missile of the aircraft according to claim 1, characterized in that: the length range of the blades of the missile rotor and the tail rotor is 180-220 mm, and the torsion angle of the blades is reduced from 15 degrees to 4 degrees from the root to the tip.

5. The working method of the integrated patrol missile of the aircraft according to claim 1, characterized in that: the energy-concentrating EFP warhead includes a hemispherical shroud and a cylindrical charge.

6. The working method of the integrated patrol missile of the aircraft according to claim 1, characterized in that: the energy-gathering jet warhead comprises a horn-shaped medicine cover and a cylindrical medicine charge.

Technical Field

The invention relates to a working method of an integrated flying patrol bomb of an aircraft, and belongs to the technical field of unmanned aerial vehicles.

Background

Along with rotor unmanned aerial vehicle technique promotes, unmanned aerial vehicle can carry on equipment weight and promote, can play more and more important effect in the modernization war. However, the existing rotor unmanned aerial vehicle flies by using a rotor, the speed of the existing rotor unmanned aerial vehicle is extremely low, and the existing rotor unmanned aerial vehicle cannot effectively meet the requirement of hitting a maneuvering target, namely, the existing rotor unmanned aerial vehicle hits a ground target, and because the speed of the existing rotor unmanned aerial vehicle is too low, a long reaction time is formed for an opponent, so that attack failure is caused.

Disclosure of Invention

The invention aims to solve the technical problems that: the defects of the technology are overcome, and the working method of the integrated flying patrol bomb of the aircraft, which integrates multiple functions of cruise detection, tracking attack, hovering striking and the like, is provided.

In order to solve the technical problems, the technical scheme provided by the invention is as follows: an operation method of an integrated flying patrol bomb of an aircraft, which is used by the method, comprises the following steps: a bullet, a bullet body and a bullet tail; the warhead comprises a housing and a camera and a shaped jet warhead disposed within the housing; the projectile body is provided with wings and a projectile body rotor wing; the bullet tail is provided with an energy-gathering EFP warhead part, an empennage and a tail rotor wing; the wings can be unfolded and retracted, and when the wings are unfolded, the wings are perpendicular to the projectile body; when the span is retracted, the wing is parallel to the projectile body; the tail wing can be unfolded and folded, and when the wing is unfolded, the tail wing is perpendicular to the missile tail; when the span is retracted, the tail extends rearward of the tail and parallel to the projectile tail; the projectile body rotor wing is connected with the projectile body through a first connecting rod; the first connecting rod can be unfolded and retracted; when the first connecting rod is unfolded, the first connecting rod is perpendicular to the projectile body; when the first connecting rod is retracted, the first connecting rod is accommodated in the elastic body and can rotate by taking the axis of the first connecting rod as an axis; a first vector control mechanism is arranged between the projectile body rotor wing and the first connecting rod; the first vector control mechanism comprises a first bracket hinged with the first connecting rod and a second bracket hinged with the first bracket; the hinge shafts of the first bracket and the second bracket are vertical to each other, and the hinge shaft of the first bracket is also vertical to the axis of the first connecting rod; the second bracket is provided with a first driving shaft for driving the elastomer rotor, the elastomer rotor is hinged on the first driving shaft and can move between positions parallel and vertical to the axis of the first connecting rod; the tail rotor wing is connected with the missile tail through a second connecting rod; the second connecting rod can be unfolded and retracted; when the second connecting rod is unfolded, the second connecting rod is vertical to the bullet tail; when the second connecting rod is retracted, the second connecting rod extends towards the rear part of the bullet tail; a second vector control mechanism is arranged between the tail rotor and the second connecting rod; the second vector control mechanism comprises a third bracket hinged with the second connecting rod and a fourth bracket hinged with the third bracket; the hinge shafts of the third bracket and the fourth bracket are vertical to each other, and the hinge shaft of the third bracket is also vertical to the axis of the second connecting rod; the fourth bracket is provided with a second driving shaft for driving the tail rotor, the tail rotor is hinged on the second driving shaft, and the tail rotor can move between positions parallel and vertical to the axis of the second connecting rod;

the integrated flying patrol bomb of the aircraft can be switched among a full-folding mode, a front flying mode and a hovering mode; when the integrated patrol missile of the aircraft is in a fully-folded mode, the wings are retracted and are in a position parallel to the missile body; the first connecting rod retracts to be accommodated in the projectile body, and the projectile body rotor wing retracts to be in a position parallel to the axis of the first connecting rod; the second connecting rod is retracted to a position extending towards the rear of the projectile tail; the tail rotor wing is retracted and is in a position parallel to the axis of the second connecting rod;

when the integrated patrol missile of the aircraft is in a forward flight mode, the wings are unfolded and are in a position vertical to the missile body; the first connecting rod is unfolded and is positioned at a position vertical to the projectile body, and the projectile body rotor wing is unfolded and is positioned at a position vertical to the axis of the first connecting rod; the second connecting rod is unfolded and is in a position vertical to the bullet tail; the tail rotor is unfolded and is in a position perpendicular to the axis of the second connecting rod; the first connecting rod and the first vector control mechanism drive the projectile rotor wing to face forwards, and the second vector control mechanism drives the tail rotor wing to face backwards;

when the integrated cruise missile of the aircraft is in a hovering mode, the wings are unfolded and are in a position vertical to the missile body; the first connecting rod is unfolded and is positioned at a position vertical to the projectile body, and the projectile body rotor wing is unfolded and is positioned at a position vertical to the axis of the first connecting rod; the second connecting rod is unfolded and is in a position vertical to the bullet tail; the tail rotor is unfolded and is in a position perpendicular to the axis of the second connecting rod; the first connecting rod and the first vector control mechanism drive the projectile rotor to face upwards, and the second vector control mechanism drives the tail rotor to face upwards.

The scheme is further improved in that: the integrated flying patrol of the aircraft is of a cylindrical structure with the caliber of 180mm and the length of 1200 mm.

The scheme is further improved in that: the wing span is 1600 mm.

The scheme is further improved in that: the length range of the blades of the missile rotor and the tail rotor is 180-220 mm, and the torsion angle of the blades is reduced from 15 degrees to 4 degrees from the root to the tip.

The scheme is further improved in that: the energy-concentrating EFP warhead includes a hemispherical shroud and a cylindrical charge.

The scheme is further improved in that: the energy-gathering jet warhead comprises a horn-shaped medicine cover and a cylindrical medicine charge.

The working method of the integrated patrol missile of the aircraft provided by the invention integrates various functions of cruise detection, attack tracking, hovering striking and the like. The integrated ammunition-aircraft system comprehensively utilizes a fixed wing aircraft technology, a rotor unmanned aerial vehicle technology, a vector propulsion technology based on accurate control of the rotation angular speed and direction of a rotor, an energy-gathering ammunition design technology, an image rapid disposal and identification technology and the like, realizes the integration of ammunition-aircraft, and can complete various functions of cruise detection, tracking attack, hovering attack and the like.

Drawings

The invention will be further explained with reference to the drawings.

Fig. 1 is a schematic structural diagram of an integrated cruise missile of an aircraft used in a preferred embodiment of the invention.

Fig. 2 is a schematic view of the fully folded mode structure of fig. 1.

Fig. 3 is a schematic structural view of the front fly mode of fig. 1.

Fig. 4 is a schematic diagram of the first and second vector control mechanisms of fig. 1.

Detailed Description