阅读说明：本技术 一种基于继电器控制的弹道修正装置 (Ballistic trajectory correcting device based on relay control ) 是由 刘通 刘士祥 于 2019-10-23 设计创作，主要内容包括：一种基于继电器控制的弹道修正装置。涉及基于继电器控制的弹道修正装置。提出了一种可用于高旋转稳定型飞行器或炮弹的弹道修正,该方案的装置在外弹道过程中依据卫星终端实现定位和弹道测量,通过控制单元计算飞行误差并发出指令,能够在弹药飞行过程中进行舵面控制并提供弹道修正力,以较低的代价和成本解决了高旋转弹体飞行时所需要的法向控制力,使传统弹药具有制导能力,提高弹药打击精度的基于继电器控制的弹道修正装置。包括中空轴、舵环、电磁继电器、衔铁和摩擦片。结构更加紧凑,驱动更加简单方便,有效减少舵机负载,利于修正弹的姿态调整,提高修正效率,使得炮弹的打击精度更高。(A ballistic trajectory correction device based on relay control. To a ballistic correction device based on relay control. The device of the scheme realizes positioning and trajectory measurement according to a satellite terminal in the outer trajectory process, calculates flight errors through a control unit and sends out instructions, control surface control can be carried out in the ammunition flying process, trajectory correction force is provided, normal control force required by high-rotation ammunition body flying is solved at low cost, traditional ammunition has guidance capability, and the ammunition hitting precision is improved. The steering gear comprises a hollow shaft, a rudder ring, an electromagnetic relay, an armature and a friction plate. The structure is compacter, and the drive is more simple and convenient, effectively reduces steering wheel load, does benefit to the posture adjustment of revising the bullet, improves and revises efficiency for the hitting precision of shell is higher.)

1. A trajectory correcting device based on relay control is characterized by comprising a hollow shaft, a rudder ring, an electromagnetic relay, an armature and a friction plate, wherein one end of the hollow shaft is connected with a projectile body or an aircraft, the other end of the hollow shaft penetrates through the rudder ring, the rudder ring is in a hollow cylindrical shape, and a pair of first canard wings with antisymmetric attack angles and a pair of second canard wings with symmetric attack angles are fixedly connected to the outer wall of the rudder ring;

the rudder ring is rotatably sleeved at the end of the hollow shaft, the armature is slidably connected at the end of the rudder ring far away from the hollow shaft, the friction plate is fixedly connected on the end face of the armature facing the hollow shaft, and the electromagnetic relay is fixedly connected at the end of the hollow shaft extending into the rudder ring and is spaced from the friction plate.

2. The relay control-based ballistic correction device according to claim 1, wherein the end surface of the rudder ring away from the hollow shaft is provided with a plurality of threaded holes, the armature is provided with a plurality of stepped holes, the stepped holes are coaxial with the threaded holes, and the stepped holes accommodate fastening bolts in threaded connection with the threaded holes; the distance between the head of the fastening bolt and the end face, far away from the hollow shaft, of the rudder ring is larger than the length of the small hole in the stepped hole, so that the armature can be connected to the end of the rudder ring in a sliding mode while the rudder ring synchronously rotates.

3. The relay control-based ballistic correction device according to claim 1, wherein an annular limiting bulge is arranged on the outer wall of the end of the hollow shaft extending into the rudder ring, and a pair of bearings sleeved outside the hollow shaft are arranged on two sides of the limiting bulge;

the rudder ring is sleeved with the bearings in a pair, two sides of the inner wall of the rudder ring are fixedly connected with a limiting ring and a bearing gland respectively, the limiting ring is attached to the bearing far away from the armature, and the bearing gland is attached to the bearing close to the armature.

4. The relay control-based ballistic correction device of claim 1, wherein the side of the hollow shaft remote from the rudder ring is externally threaded.

Technical Field

The invention relates to a ballistic trajectory correction device based on relay control, and belongs to the technical field of control devices for aircrafts or correction bullets.

Background

After the traditional ammunition is launched out of a chamber, because the ammunition lacks the capability of trajectory active control, the movement track of the ammunition in the outer trajectory process cannot be autonomously controlled except weather interference, so that the traditional ammunition is poor in precision, large in dispersion and high in cost-efficiency ratio in operation, and a huge amount of ammunition needs to be consumed to carry out carpet type firepower coverage so as to destroy a target. This not only provides the challenge for the logistics supply of ammunition, has reduced the mobility on the battlefield more greatly, has improved the risk of fighting, causes the harmful effects for the mission of fighting.

Modern war mostly occurs in the form of local war or antiterrorist action, requiring precise surgical approach to combat. The traditional striking mode brings inestimable safety problems, causes casualties of civilian and causes a great deal of pollution to the environment. The above negative factors and consequences place an urgent need for ammunition with ballistic control or precision percussion capabilities, as well as a need for retrofit upgrades to conventional ammunition. Meanwhile, the requirements of the modern war on the striking precision and low-cost control of ammunition are increasingly strengthened, so that a correction bullet with actively controlled trajectory is produced in a simple and effective mode. The ballistic projectile is modified on the basis of the common projectile, so that a great deal of research, development, design and manufacturing expenses are saved, and the ballistic projectile is a promising low-cost guided ammunition scheme. At present, two-dimensional trajectory correction bullets released by various countries mainly adopt two control mechanisms: pulse motor and duck rudder control. For an aircraft or a cannonball rotating at a high speed, the flight stability is ensured by utilizing the self-rotation, and if the speed and the position of a rudder wing are controlled, the high rotation speed of a motor is required to overcome the self-high rotation speed (often exceeding 18000 revolutions per minute) of a bomb body according to a conventional method, so that the great difficulty is obviously caused.

As shown in fig. 1, the conventional ballistic trajectory modification device has a cross-shaped duck rudder configuration, in which a group of duck wings have anti-symmetric attack angles, and an aerodynamically induced rotation moment is generated when flying in the windward direction; the other group of canard wings have symmetrical attack angles and can generate normal control force to change the flight path of the projectile body. Therefore, the trajectory correcting device is arranged on a high-rotation aircraft or a shell body, the balance or driving rotation can be considered under the pneumatic induction moment and the damping action of a steering engine on the shell body, the posture and the speed of the duck rudder are greatly controlled under the comprehensive action of the pneumatic moment and the steering engine, and the adjustment of the magnitude and the direction of the normal force received by the flying shell body is realized. At present, the correction bomb of the background generally adopts a generator scheme, needs a complex control loop, load matching and a transmission speed reducing mechanism matched with the generator scheme, has large volume and large size, and has adverse effects on the integrated design and flight characteristics of the whole control system.

Disclosure of Invention

Aiming at the problems, the invention provides a trajectory correction device based on relay control, which can be used for a high-rotation-stability aircraft or a shell, the device of the scheme realizes positioning and trajectory measurement according to a satellite terminal in the outer trajectory process, calculates flight errors through a control unit and sends out instructions, can control a control surface and provide trajectory correction force in the ammunition flight process, solves the normal control force required by the high-rotation ammunition body in flight at lower cost, enables the traditional ammunition to have guidance capability, and improves the ammunition striking precision.

The technical scheme of the invention is as follows: the aircraft rudder ring is hollow and cylindrical, and a pair of canard wings with antisymmetric attack angles and a pair of canard wings with symmetric attack angles are fixedly connected to the outer wall of the rudder ring;

the rudder ring is rotatably sleeved at the end of the hollow shaft, the armature is slidably connected at the end of the rudder ring far away from the hollow shaft, the friction plate is fixedly connected on the end face of the armature facing the hollow shaft, and the electromagnetic relay is fixedly connected at the end of the hollow shaft extending into the rudder ring and is spaced from the friction plate.

The end face, away from the hollow shaft, of the rudder ring is provided with a plurality of threaded holes, the armature is provided with a plurality of stepped holes, the stepped holes and the threaded holes are coaxial, and fastening bolts in threaded connection with the threaded holes are accommodated in the stepped holes; the distance between the head of the fastening bolt and the end face, far away from the hollow shaft, of the rudder ring is larger than the length of the small hole in the stepped hole, so that the armature can be connected to the end of the rudder ring in a sliding mode while the rudder ring synchronously rotates.

An annular limiting bulge is arranged on the outer wall of the end of the hollow shaft extending into the rudder ring, and a pair of bearings sleeved outside the hollow shaft are arranged on two sides of the limiting bulge;

the rudder ring is sleeved with the bearings in a pair, two sides of the inner wall of the rudder ring are fixedly connected with a limiting ring and a bearing gland respectively, the limiting ring is attached to the bearing far away from the armature, and the bearing gland is attached to the bearing close to the armature.

And one side of the hollow shaft, which is far away from the rudder ring, is provided with an external thread.

The invention has the beneficial effects that: the electromagnetic relay is adopted to replace a motor of a traditional steering engine, the structure is more compact, the driving is simpler and more convenient, the steering engine load is effectively reduced, the posture adjustment of the correction projectile is facilitated, the correction efficiency is improved, and the striking precision of the projectile is higher.

Drawings

Figure 1 is a background art schematic of the present invention,

figure 2 is an axial cross-sectional view of the invention,

FIG. 3 is a perspective view of the present invention;

in the figure, 1 is a hollow shaft, 10 is a limit bulge, 2 is a rudder ring, 20 is a limit ring, 3 is a bearing, 4 is a fastening bolt, 5 is an armature, 6 is a friction plate, 7 is an electromagnetic relay, and 8 is a bearing gland.

Detailed Description

The invention is shown in figures 1-3, and comprises a hollow shaft 1, a rudder ring 2, an electromagnetic relay 7, an armature 5 and a friction plate 6, wherein one end of the hollow shaft 1 is connected with a projectile or an aircraft, the other end of the hollow shaft penetrates through the rudder ring 2, the rudder ring 2 is in a hollow cylinder shape, and a pair of canard fins with anti-symmetric attack angles and a pair of canard fins with symmetric attack angles are fixedly connected to the outer wall of the rudder ring 2; thus, because one pair of canard wings has an anti-symmetric attack angle, the aerody-induced rotation moment is generated when the canard wings fly towards the wind; because the pair of the second canard wings have symmetrical attack angles, normal control force can be generated to change the flight trajectory of the projectile body when the projectile flies windward;

the rudder ring 2 is rotatably sleeved at the end of the hollow shaft 1, the armature 5 is slidably connected at the end of the rudder ring far away from the hollow shaft 1, the friction plate 6 is fixedly connected on the end face of the armature 5 facing the hollow shaft 1, and the electromagnetic relay 7 is fixedly connected at the end of the hollow shaft 1 extending into the rudder ring 2 and is spaced from the friction plate 6.

The end face, away from the hollow shaft, of the rudder ring is provided with a plurality of threaded holes, the armature is provided with a plurality of stepped holes, the stepped holes and the threaded holes are coaxial, fastening bolts 4 in threaded connection with the threaded holes are accommodated in the stepped holes, and the distance between the heads of the fastening bolts and the end face, away from the hollow shaft, of the rudder ring is larger than the length of the small holes in the stepped holes, so that the armature can be connected to the end of the rudder ring in a sliding manner while synchronously rotating with the rudder ring.

Thus, when the electromagnetic relay is not electrified, the hollow shaft rotates synchronously with the projectile body or the aircraft, the rudder ring rotates in the direction opposite to the hollow shaft due to the fact that the rudder ring is separated from the projectile body through the bearing, and the electromagnetic relay and the friction plate are kept in a separated state due to the existence of the gap.

When the speed and the position of the rudder ring need to be adjusted to generate pneumatic control force in a specific direction, the electromagnetic relay can be driven to be electrified, so that the armature slides towards the electromagnetic relay under the influence of adsorption force, the friction plate is forced to be in contact with the electromagnetic relay, and braking torque is applied to the rudder ring through the friction plate and the armature, so that the speed and the position of the rudder ring are adjusted under the comprehensive action of pneumatic induction torque and braking torque; the rotating state of the rudder ring is changed, the rudder ring is used for controlling the speed and the position of a control surface, and the aerodynamic force generated by the rudder wing is changed, so that the flying attitude of the aircraft is adjusted, the flying track is controlled, and the purpose of correcting the flying track is achieved.

Wherein, the control moment is generated by the suction of the electromagnetic relay, the armature and the friction plate, so as to change the rotation state of the rudder ring. The magnitude of the control torque is changed by changing the electrifying action time length of the current in the electromagnetic relay and the magnitude of the voltage amplitude. A friction plate is adopted between the armature and the electromagnetic relay to improve the contact condition. The hollow shaft for connecting the projectile body and the steering engine is of a hollow structure, so that a lead and signal wires required by other parts can penetrate through the inside of the shaft, and meanwhile, the weight of the steering engine system is effectively reduced.

An annular limiting bulge 10 is arranged on the outer wall of the end of the hollow shaft 1 extending into the rudder ring 2, and a pair of bearings 3 sleeved outside the hollow shaft 1 are arranged on two sides of the limiting bulge 10;

the rudder ring 2 is sleeved with the bearing 3, two sides of the inner wall of the rudder ring 2 are fixedly connected with a limiting ring 20 and a bearing gland 8 respectively, the limiting ring 20 is attached to one side, away from the armature 5, of the bearing 3, and the bearing gland 8 is attached to one side, away from the armature 5, of the bearing 3. Therefore, one bearing is stably accommodated between the limiting bulge and the limiting ring, and the other bearing is stably accommodated between the bearing gland and the limiting bulge; therefore, the structural stability of the scheme can be ensured, and meanwhile, the assembly and the installation of the scheme are more convenient and efficient.

And an external thread is arranged on one side of the hollow shaft 1 far away from the rudder ring 2. So that the hollow shaft is screwed to achieve a stable connection with the projectile or aircraft.