阅读说明：本技术 飞行器级间分离结构与方法 (Aircraft interstage separation structure and method ) 是由 刘劲松 胡洁 康海峰 孙文钊 蒋君庭 江玉刚 曾清香 施臣钢 于 2019-10-31 设计创作，主要内容包括：本发明提供了一种飞行器级间分离结构与方法,包括级间舱、弹簧分离机构和切割索组件,级间舱两端分别连接助推级和飞行器主级,弹簧分离机构包括底板、外套筒、内套筒、承力板以及弹簧,切割索组件包括切割索、电发火管以及火焰雷管；底板连接外套筒,承力板连接内套筒,外套筒套装在内套筒外面,弹簧安装在内套筒内部；底板连接级间舱的一端,承力板连接级间舱的另一端；切割索上设置有电发火管以及火焰雷管,电发火管连接火焰雷管,切割索设置在级间舱上。本发明结构简单合理,通过切割索组件将助推级与飞行器主级之间的连接约束解除的同时也解除了弹簧分离机构的约束,弹簧力释放弹力推开助推级与飞行器主级,使得助推级与飞行器主级快速分离。(The invention provides an aircraft interstage separation structure and method, which comprises an interstage cabin, a spring separation mechanism and a cutting cable assembly, wherein two ends of the interstage cabin are respectively connected with a boosting stage and an aircraft main stage; the bottom plate is connected with an outer sleeve, the bearing plate is connected with an inner sleeve, the outer sleeve is sleeved outside the inner sleeve, and the spring is arranged inside the inner sleeve; the bottom plate is connected with one end of the interstage cabin, and the bearing plate is connected with the other end of the interstage cabin; the cutting cable is provided with an electric ignition tube and a flame detonator, the electric ignition tube is connected with the flame detonator, and the cutting cable is arranged on the interstage cabin. The invention has simple and reasonable structure, removes the connection constraint between the boosting stage and the main stage of the aircraft by the cutting cable assembly, simultaneously removes the constraint of the spring separation mechanism, releases the elastic force by the spring force to push the boosting stage and the main stage of the aircraft, and leads the boosting stage to be quickly separated from the main stage of the aircraft.)

1. The interstage separation structure of the aircraft comprises an interstage cabin (8), wherein two ends of the interstage cabin (8) are respectively connected with a boosting stage and a main stage of the aircraft, and the interstage separation structure is characterized by further comprising a spring separation mechanism and a cutting cable assembly, wherein the spring separation mechanism comprises a bottom plate (1), an outer sleeve (2), an inner sleeve (3), a bearing plate (4) and a spring (5), and the cutting cable assembly comprises a cutting cable (6), an electric ignition tube (7) and a flame detonator;

the bottom plate (1) is connected with the outer sleeve (2), the bearing plate (4) is connected with the inner sleeve (3), the outer sleeve (2) is sleeved outside the inner sleeve (3), and the spring (5) is arranged inside the inner sleeve (2); the bottom plate (1) is connected with one end of the interstage cabin (8), and the bearing plate (4) is connected with the other end of the interstage cabin (8);

the cutting rope (6) is provided with an electric ignition tube (7) and a flame detonator, the electric ignition tube (7) is connected with the flame detonator, and the cutting rope (6) is arranged on the interstage compartment (8).

2. The aircraft interstage separation structure according to claim 1, characterized in that the cutting rope (6) is annular and is arranged in the circumferential direction of the interstage compartment (8).

3. The aircraft interstage separation structure according to claim 1, characterized in that said electric ignition tubes (7) are two.

4. The aircraft interstage separation structure according to claim 1, characterized in that the spring (5) is constrained in a compressed state by the base plate (1) and the force bearing plate (4) in the inner sleeve (3).

5. The aircraft interstage separation structure according to claim 1, characterized in that the inner sleeve (3) and the outer sleeve (2) are coaxially connected and matched in diameter, the inner sleeve (3) being movable along the outer sleeve (2) axis.

6. The aircraft interstage separation structure according to claim 1, characterized in that it further comprises a control system connected to an electric squib (7).

7. An aircraft interstage separation method, comprising the steps of:

step 1: the control system sends a separation ignition signal to the electric ignition tube (7);

step 2: the electric ignition tube (7) receives the ignition signal and then detonates to output flame to detonate the flame detonator;

and step 3: the flame detonator works to detonate the cutting cable (6), the cutting cable (6) works to cut the inter-stage cabin (8), and the connection constraint between the boosting stage and the main stage of the aircraft is relieved;

and 4, step 4: the interstage compartment (8) is cut, the connection constraint between the bottom plate (1) and the bearing plate (4) is released, the compressed spring (5) releases the spring force to generate thrust, and the main stage of the aircraft is pushed to be separated from the boosting stage.

8. The aircraft interstage separation method of claim 7, wherein the aircraft interstage separation structure of any one of claims 1 to 6 is used.

Technical Field

The invention relates to the technical field of aircraft separation, in particular to an aircraft interstage separation structure and method.

Background

At present, remote air defense missiles are generally improved and designed based on mature missile platforms, and the requirement of remote air defense is mainly met by adding a primary booster, so that the missiles generally adopt a general scheme of 'primary plus boosting', are separated from the primary missiles after the boosting engine finishes working, and are statically stable before separation; the separated missile main-level missile body is static and unstable; and during separation, the flying Mach number of the missile is about 2.3-2.6. The characteristics of the projectile body are rapidly changed from static stability to static instability in a short time before and after separation, and the interference torque generated by the disturbance of the projectile body is very severe under the condition of high flying Mach number; therefore, strong disturbance interstage separation and stable control are one of the main key technologies, and further analysis shows that an interstage separation structure with small disturbance force and safe and rapid separation is a technical key point.

The patent document with the publication number of CN203461147U discloses an interstage separation device of an aircraft, which is arranged on an interstage casing of the aircraft and comprises a baffle plate, a protective cover and a cutting cable assembly; the interstage casing comprises a weakening groove extending along one side of the interstage casing in the circumferential direction, and a mounting positioning groove extending along the other side of the interstage casing in the circumferential direction and opposite to the weakening groove; the cutting rope assembly is arranged in the installation positioning groove; the protective cover is fixed on the outer side of the interstage shell and completely covers the cutting rope assembly; a baffle is secured outside the interstage casing and the cutting cord assembly falls completely into a projection of the baffle into the interstage casing. Although the scheme has a simple structure, instability caused by interference torque generated by projectile body disturbance during separation cannot be avoided, and the characteristic of rapid separation is not provided.

Disclosure of Invention

In view of the shortcomings of the prior art, it is an object of the present invention to provide an aircraft interstage separation structure and method.

According to one aspect of the invention, the interstage separation structure of the aircraft comprises an interstage cabin, a spring separation mechanism and a cutting cable assembly, wherein two ends of the interstage cabin are respectively connected with a booster stage and a main stage of the aircraft, the spring separation mechanism comprises a bottom plate, an outer sleeve, an inner sleeve, a bearing plate and a spring, and the cutting cable assembly comprises a cutting cable, an electric ignition tube and a flame detonator;

the bottom plate is connected with the outer sleeve, the bearing plate is connected with the inner sleeve, the outer sleeve is sleeved outside the inner sleeve, and the spring is arranged inside the inner sleeve; the bottom plate is connected with one end of the interstage cabin, and the bearing plate is connected with the other end of the interstage cabin;

the cutting cable is provided with an electric ignition tube and a flame detonator, the electric ignition tube is connected with the flame detonator, and the cutting cable is arranged on the interstage cabin.

Preferably, the cutting rope is annular and is arranged in the circumferential direction of the interstage compartment.

Preferably, the number of the electric ignition tubes is two.

Preferably, the spring is restrained in a compressed state by the bottom plate and the bearing plate in the inner sleeve.

Preferably, the inner sleeve and the outer sleeve are coaxially connected and matched in diameter, and the inner sleeve is capable of moving along the axis of the outer sleeve.

Preferably, the electric heating device further comprises a control system, and the control system is connected with the electric heating tube.

According to another aspect of the invention, there is provided an aircraft interstage separation method comprising the steps of:

step 1: the control system sends a separation ignition signal to the electric ignition tube;

step 2: the electric ignition tube receives the ignition signal and then detonates to output flame to detonate the flame detonator;

and step 3: the flame detonator works to detonate the cutting cable, the cutting cable works to cut the inter-stage cabin, and the connection constraint between the boosting stage and the main stage of the aircraft is removed;

and 4, step 4: the interstage compartment is cut, the connection constraint between the bottom plate and the bearing plate is released, the compressed spring releases the spring force, thrust is generated, and the main stage of the aircraft is pushed to be separated from the boosting stage.

Preferably, the aircraft interstage separation structure is adopted.

Compared with the prior art, the invention has the following beneficial effects:

1. the invention has simple and reasonable structure, combines the spring separation mechanism and the cutting cable assembly, removes the connection constraint between the boosting stage and the main stage of the aircraft through the cutting cable assembly, removes the constraint of the spring separation mechanism at the same time, and releases elastic force to push the boosting stage and the main stage of the aircraft, so that the boosting stage and the main stage of the aircraft are quickly separated.

2. According to the spring separation mechanism, the inner sleeve and the outer sleeve are arranged, so that the accurate control of the separation direction is realized, the disturbance of the main stage of the aircraft during separation is reduced, and the separation stability is improved.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a schematic structural view of the spring release mechanism of the present invention.

FIG. 3 is a schematic view of an angled construction of the cutting cord assembly of the present invention.

FIG. 4 is a schematic view of another angle configuration of the cutting cord assembly of the present invention.

FIG. 5 is a cross-sectional structural view of the cutting cord assembly of the present invention.

The figures show that:

spring 5 of bottom plate 1

Outer sleeve 2 cutting cord 6

Inner sleeve 3 electric ignition tube 7

Bearing plate 4-stage cabin 8

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

According to the invention, as shown in fig. 1-5, the interstage separation structure of the aircraft comprises an interstage cabin 8, wherein two ends of the interstage cabin 8 are respectively connected with a booster stage and a main stage of the aircraft, and further comprises a spring separation mechanism and a cutting cable assembly, wherein the spring separation mechanism comprises a bottom plate 1, an outer sleeve 2, an inner sleeve 3, a bearing plate 4 and a spring 5, and the cutting cable assembly comprises a cutting cable 6, an electric ignition tube 7 and a flame detonator; the bottom plate 1 is connected with an outer sleeve 2, the bearing plate 4 is connected with an inner sleeve 3, the outer sleeve 2 is sleeved outside the inner sleeve 3, and the spring 5 is arranged inside the inner sleeve 2; the bottom plate 1 is connected with one end of the interstage cabin 8, and the bearing plate 4 is connected with the other end of the interstage cabin 8; the cutting cable 6 is provided with an electric ignition tube 7 and a flame detonator, the electric ignition tube 7 is connected with the flame detonator, and the cutting cable 6 is arranged on the interstage cabin 8. The invention meets the requirements of quick response and small impact force in the two-stage separation process of the aircraft, has compact structure, small occupied space and small disturbance force, and various performance indexes of interstage separation meet the design requirements, thereby ensuring that the boosting stage is smoothly separated from the main stage of the aircraft. The cutting rope assembly and the spring separating mechanism are used cooperatively, and domestic examples of realizing interstage separation by using the cutting rope are more, but the cutting rope assembly and the spring separating mechanism are rarely used cooperatively at the same time.

The cutting wire 6 is annular and arranged in the circumferential direction of the interstage compartment 8. The number of the electric ignition tubes 7 is two, and any one of the two electric ignition tubes 7 can detonate the cutting rope to realize the final function. The spring 5 is restrained in a compressed state by the inner sleeve 3 through the bottom plate 1 and the bearing plate 4, and preferably, the spring 5 can generate 4000N of spring thrust to push the inner sleeve 3 and the outer sleeve 2 to separate, so that the separation of the boosting stage and the main stage of the aircraft is realized. The inner sleeve 3 and the outer sleeve 2 are coaxially connected and have diameters matched with each other, the inner sleeve 3 can move along the axis of the outer sleeve 2, and preferably, the outer diameter of the inner sleeve 3 is smaller than or equal to the inner diameter of the outer sleeve 2, so that the inner sleeve 3 cannot shake in the outer sleeve 2 along the radial direction and can slide smoothly in the outer sleeve 2 along the axial direction. The arrangement of the outer sleeve 2 and the inner sleeve 3 can not only mount the spring 5, but also restrict the stroke track of the spring 5. And the control system is connected with the electric ignition tube 7.

The invention provides an aircraft interstage separation method, in particular an aircraft interstage separation method adopting the aircraft interstage separation structure, which comprises the following steps:

step 1: the control system sends a separation ignition signal to the electric ignition tube 7;

step 2: the electric ignition tube 7 receives the ignition signal and then detonates to output flame to detonate the flame detonator;

and step 3: the flame detonator works to detonate the cutting cable 6, the cutting cable 6 works to cut the inter-stage cabin 8, and the connection constraint between the boosting stage and the main stage of the aircraft is removed;

and 4, step 4: the inter-stage cabin 8 is cut, the connection constraint between the bottom plate 1 and the bearing plate 4 is released, the compressed spring 5 releases the spring force, thrust is generated, and the main stage of the aircraft is pushed to be separated from the boosting stage.

The preferred embodiment:

the invention is applied to the interstage separation of the guided missile, in particular to the interstage separation of the guided missile booster and the guided missile main stage, and comprises the following steps: the cutting cable assembly consists of two electric ignition tubes 7 and a set of cutting cables 6; the spring separating mechanism consists of a bottom plate 1, a bearing plate 4, an inner sleeve 3, an outer sleeve 2 and a spring 5;

the two electric ignition tubes 7 are fixedly arranged on the cutting rope 6 and can receive an ignition signal of a control system; the electric ignition tube 7 is detonated to output flame to detonate a flame detonator, the flame detonator works, the cutting rope assembly is fixed on the interstage cabin shell, receives an initiation signal of the electric ignition tube 7, generates blasting, and cuts off the shell of the interstage cabin 8.

The spring separating mechanism is installed on a shell of the interstage cabin 8, a bottom plate 1 of the spring separating mechanism is connected with the shell of the interstage cabin 8 through a screw, a bearing plate 4 of the spring separating mechanism acts on a front end frame of the shell of the interstage cabin 8 through pressure generated by a spring 5, an outer sleeve 2 of the spring separating mechanism is installed on the bottom plate 1 through a screw, an inner sleeve 3 of the spring separating mechanism is installed on the bearing plate 4 through a screw, and the spring 5 of the spring separating mechanism is installed in the inner sleeve 3. The plate 1 is a bottom plate 1 for connecting the spring separating mechanism with the interstage compartment 8 housing, and is used for supporting the spring separating mechanism and connecting the spring separating mechanism with the interstage compartment 8 housing. The bearing plate 4 is an acting plate of spring thrust of the spring separation mechanism, and the bearing plate 4 pushes the missile main stage under the pushing of the spring force, so that the booster is quickly separated from the missile main stage. The spring 5 is arranged in the inner sleeve 3 of the spring separation mechanism, the spring is compressed to generate 4000N of spring thrust, and when the constraint of the spring separation mechanism is relieved, the spring force is released to generate 4000N of thrust to push the booster to be quickly separated from the main stage of the missile. The outer sleeve 2 and the inner sleeve 3 are used for installing the spring 5 and restraining the travel track of the spring 5, and in the case that the restraint is released after the cutting cable 6 is initiated to cut the shell of the inter-stage cabin 8, the spring 5 generates pushing force, and the outer sleeve 2 and the inner sleeve 3 are pushed away under the pushing force of the spring 5.

When the electric ignition tube 7 receives a separation ignition signal sent by the control system, the electric ignition tube 7 detonates and outputs flame to ignite a flame detonator, the flame detonator works, the flame detonator ignites the cutting cable 6, the cutting cable 6 works to cut the shell of the inter-stage cabin 8, the connection constraint between the booster and the main stage of the missile is removed, meanwhile, the constraint of the spring separation mechanism is removed, the spring force is released, and thrust is generated to push the main stage of the missile to be quickly separated from the boosting stage.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.