阅读说明：本技术 一种星箭分离解锁动作器 (Star and arrow separation unblock actor ) 是由 张亮 杨浩亮 孙志超 张毅 刘千 于 2021-09-07 设计创作，主要内容包括：本发明创造提供了一种星箭分离解锁动作器,包括动作器外筒以及安装在动作器外筒下端的尾部端盖；在动作器外筒内安装有导向座和导向架,在导向座内安装有固定座,固定座内安装有拔销；所述导向架包括与导向座配合的安装部、以及安装部内部设置的导向柱；在导向柱上安装有弹性件,该弹性件上端抵住所述拔销；在导向架内腔安装有用于驱动固定座移动的记忆合金丝；所述尾部端盖上安装有为记忆合金丝通电的航空插头。本发明创造采用封闭集成化设计,结构紧凑,集成度高,拔销动作时稳定性极佳,同时,对复杂电磁环境耐受性好,使用维护方便、解锁速度快、工作可靠性高。(The invention provides a satellite-rocket separation unlocking actuator, which comprises an actuator outer cylinder and a tail end cover arranged at the lower end of the actuator outer cylinder; a guide seat and a guide frame are arranged in the outer cylinder of the actuator, a fixed seat is arranged in the guide seat, and a pull pin is arranged in the fixed seat; the guide frame comprises an installation part matched with the guide seat and a guide post arranged in the installation part; an elastic piece is arranged on the guide post, and the upper end of the elastic piece is propped against the pull pin; a memory alloy wire for driving the fixed seat to move is arranged in the inner cavity of the guide frame; and an aviation plug electrified for the memory alloy wire is arranged on the tail end cover. The invention adopts a closed integrated design, has compact structure, high integration level, excellent stability during pin pulling action, good tolerance to complex electromagnetic environment, convenient use and maintenance, high unlocking speed and high working reliability.)

1. The utility model provides a satellite and rocket separation unblock motion ware which characterized in that: comprises an actuator outer cylinder and a tail end cover arranged at the lower end of the actuator outer cylinder;

a guide seat and a guide frame are arranged in the outer cylinder of the actuator, a fixed seat is arranged in the guide seat, and a pull pin is arranged in the fixed seat; the guide frame comprises an installation part matched with the guide seat and a guide post arranged in the installation part;

an elastic piece is arranged on the guide post, and the upper end of the elastic piece is propped against the pull pin; a memory alloy wire for driving the fixed seat to move is arranged in the inner cavity of the guide frame; and an aviation plug electrified for the memory alloy wire is arranged on the tail end cover.

2. The star-arrow separation unlocking actuator according to claim 1, characterized in that: the guide post is arranged in the center of the mounting portion.

3. The star-arrow separation unlocking actuator according to claim 1, characterized in that: the guide seat, the guide frame and the actuator outer cylinder are all made of insulating materials.

4. The star-arrow separation unlocking actuator according to claim 1, characterized in that: the fixing seat is in sliding fit with the guide seat, a limiting table is arranged at the upper end of the inner wall of the fixing seat, and a positioning table matched with the limiting table is arranged at the bottom of the pull pin.

5. The star-arrow separation unlocking actuator according to claim 1 or 4, characterized in that: and the inner wall of the upper end of the outer barrel of the actuator is provided with an installation platform matched with the fixed seat.

6. The star-arrow separation unlocking actuator according to claim 1, characterized in that: the end cover is installed on the actuator outer cylinder in a threaded mode.

7. The star-arrow separation unlocking actuator according to claim 1, characterized in that: the lower end of the guide seat is inserted into the upper end of the mounting part.

8. The star-arrow separation unlocking actuator according to any one of claims 1 to 7, characterized in that: and a connecting flange is arranged on the outer side of the outer cylinder of the actuator.

9. The star-arrow separation unlocking actuator according to any one of claims 1 to 7, characterized in that: the elastic part adopts a spring which is sleeved on the guide post.

Technical Field

The invention belongs to the technical field of aerospace, and particularly relates to a satellite-rocket separation unlocking actuator.

Background

The satellite and rocket separation unlocking driving facility generally realizes connection and unlocking through a connection unlocking device, and realizes separation movement of the payload and the carrier rocket through a separation energy device. The existing connecting and unlocking structure is complex, the use reliability is low, the requirements on the processing precision and the processing technology of parts are very strict, the processing cost is high, and the processing and manufacturing difficulty is high. Accordingly, there is a need for an improved release mechanism in existing dissociative lock devices.

Disclosure of Invention

In view of this, the invention provides a star-arrow separation unlocking actuator, which aims to overcome the defects in the prior art.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

a star-arrow separation unlocking actuator comprises an actuator outer cylinder and a tail end cover arranged at the lower end of the actuator outer cylinder; a guide seat and a guide frame are arranged in the outer cylinder of the actuator, a fixed seat is arranged in the guide seat, and a pull pin is arranged in the fixed seat;

the guide frame comprises an installation part matched with the guide seat and a guide post arranged in the installation part; an elastic piece is arranged on the guide post, and the upper end of the elastic piece is propped against the pull pin;

a memory alloy wire for driving the fixed seat to move is arranged in the inner cavity of the guide frame; and an aviation plug electrified for the memory alloy wire is arranged on the tail end cover.

Further, the guide post is arranged in the installation department center, the installation department bottom is the blind end, and the guide post is arranged in the bottom center.

Furthermore, the guide seat, the guide frame and the actuator outer cylinder are all made of insulating materials.

Further, fixing base and guide holder sliding fit are equipped with spacing platform in the upper end of fixing base inner wall, the pull pin bottom be equipped with spacing platform complex location platform.

Furthermore, the inner wall of the upper end of the outer barrel of the actuator is provided with an installation platform matched with the fixed seat.

Further, the end cover is installed on the outer cylinder of the actuator in a threaded mode.

Furthermore, the lower end of the guide seat is inserted into the upper end of the mounting part.

Furthermore, a connecting flange is arranged on the outer side of the outer cylinder of the actuator.

Further, the elastic part adopts a spring which is sleeved on the guide post.

Compared with the prior art, the invention has the following advantages:

the invention adopts a closed integrated design, has compact structure, high integration level, excellent stability during pin pulling action, good tolerance to complex electromagnetic environment, convenient use and maintenance, high unlocking speed and high working reliability.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the invention without limitation. In the drawings:

FIG. 1 is a schematic view of the external structure of the present invention;

FIG. 2 is a cross-sectional view of the invention;

FIG. 3 is a schematic view of the pull pin of FIG. 2 after retraction;

FIG. 4 is a schematic view of FIG. 2 with the actuator outer barrel and end cap removed;

FIG. 5 is a schematic view of FIG. 1 with the actuator outer barrel and end cap removed;

FIG. 6 is a schematic view of the present invention without the actuator outer cylinder, the end cap and the guide seat;

FIG. 7 is a schematic view of FIG. 4 with the guide housing removed;

FIG. 8 is a schematic view of a guide frame in an embodiment of the invention;

fig. 9 is a schematic perspective view of a guide frame in an embodiment of the present invention.

Detailed Description

It should be noted that the embodiments and features of the embodiments of the present invention may be combined with each other without conflict.

In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings, which are merely for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be construed as limiting the invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.

In the description of the invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "connected" and "connected" are to be construed broadly, e.g. as being fixed or detachable or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.

The invention will be described in detail with reference to the following embodiments with reference to the attached drawings.

A star-arrow separation unlocking actuator is shown in figures 1 to 9 and comprises an actuator outer cylinder 1 and a tail end cover 2 arranged at the lower end of the actuator outer cylinder. Typically, the end cap is threadably mounted on the actuator outer barrel. The outer side of the outer cylinder of the actuator is provided with a connecting flange 3, so that the unlocking actuator is convenient to mount. A guide seat 4 and a guide frame 5 are arranged in the outer cylinder of the actuator, a fixed seat 6 is arranged in the guide seat, and a pull pin 7 is arranged in the fixed seat.

The guide frame comprises a mounting part 8 matched with the guide seat and a guide post 9 arranged in the mounting part; an elastic piece 10 is arranged on the guide post, and the upper end of the elastic piece is propped against the pull pin; a memory alloy wire 11 for driving the fixed seat to move is arranged in the inner cavity of the guide frame; and an aviation plug 12 electrified to the memory alloy wire is arranged on the tail end cover. The connection of the plug and the memory alloy wire is the content of the prior art, and the details are not repeated here, and the memory alloy wire is taken as power to realize reliable separation and contraction actions.

The guide seat, the guide frame and the actuator outer cylinder are all made of insulating materials, so that the unlocking actuator has good insulating performance. The guide post is arranged in the center of the mounting portion. The installation department bottom is sealed by back cover 13, and the guide post is arranged in back cover center department, and is preferred, and guide post, back cover, installation department are integrated into one piece preparation, and structural stability is better.

The tail part of the pulling pin is provided with a positioning section 14 and an auxiliary positioning section 15, the diameter of the positioning section is larger than that of the pulling pin main body 16, the diameter of the auxiliary positioning section is larger than that of the positioning section, an auxiliary positioning table 17 is formed at the joint of the auxiliary positioning section and the positioning section, and a positioning table 18 is formed between the positioning section and the pulling pin main body. The fixed seat is in sliding fit with the guide seat, the upper end of the inner wall of the fixed seat is provided with a limiting table 19, and the positioning table at the bottom of the pull pin is matched with the limiting table. The upper end of the inner wall of the guide seat is provided with an installation table 20, and the auxiliary positioning table at the bottom of the pulling pin is matched with the installation table, so that the positioning is accurate, the structure is stable, and the reliability is high.

Under normal state (when the memory alloy wire is not powered on), the upper end surface of the fixed seat is abutted against the lower surface of the mounting table, at the moment, a small gap (0.01-0.2mm) is allowed between the upper end surface of the auxiliary positioning table and the lower surface of the mounting table, and the buffer can be realized during pin pulling action.

Meanwhile, as indicated in the background art, the machining precision of each part in the star-arrow separation unlocking control is higher, in the invention, the gap arranged between the auxiliary positioning table and the mounting table can avoid the adsorption force between two workpieces possibly generated due to higher machining precision, and because the resistance between the auxiliary positioning table and the mounting table in the separation process is eliminated, the instantaneous impact can not be generated, so the pin pulling opening and closing action is stable and reliable.

It should be pointed out that, because the location section that the pin pulling afterbody set up, supplementary location section use the fixing base to support the basis simultaneously, the guide holder and shell actuator urceolus upper end are as the support basis of pin pulling main part simultaneously to, above-mentioned actuator urceolus upper end inner wall is equipped with guide holder complex concave station 21, ensures guide holder installation accuracy and installation stability.

Above-mentioned structural design forms multistage location and spacing to the pulling pin in other words for the pulling pin position keeps the precision high, and structural stability is splendid.

The lower end of the guide seat is inserted into the upper end of the mounting part. For example, the lower end of the guide seat is provided with a matching section 22, the upper end of the mounting part is provided with a matching structure 23 matched with the matching section, the guide seat and the mounting part are stably matched, the continuity of the inner wall of the guide seat and the inner wall of the mounting part is ensured, the connection is smooth, the capacity of bearing radial load and axial load is better, and the stability of the whole structure is good.

In an alternative embodiment, the matching structure comprises four vertical plates 24 which are symmetrically arranged, a matching seat 25 is machined at the lower end of each vertical plate, and a plug 27 which is matched with each vertical plate is machined at the lower end of the fixing seat. Specifically, a matching surface 26 matched with the inner surface of the plug at the lower end of the fixing seat is processed at the upper end of each vertical plate. The inner wall of the outer barrel of the actuator is provided with grooves matched with the vertical plate matching seat bodies, so that the stability of the guide frame matched with the outer barrel of the actuator can be guaranteed to the maximum extent.

The elastic piece adopts a spring which is sleeved on the guide post. In an alternative embodiment, the diameter of the guiding column increases from top to bottom, i.e. the guiding column is tapered, and the diameter of the guiding column increases gradually from the free end to the end close to the back cover. When the spring is compressed, the elastic acting force of the spring is changed linearly, so that the stability of the pin pulling action can be effectively guaranteed.

In an alternative embodiment, the fixing base is a quadrangular prism structure matched with four vertical plates, a groove 28 is formed at each edge position (the grooves formed on the two adjacent side surfaces and the top surface of the edge are communicated to form a groove for accommodating the memory alloy wires), the memory alloy wires at the four corners of the fixing base respectively bypass the fixing base along the groove, so that uniform force application to the fixing base is realized, and the stability of pin pulling action can be effectively improved. The depth of the groove is slightly larger than the diameter of the memory alloy wire, so that the memory alloy wire is prevented from being immersed into the groove and interfering with other structural parts.

In the process of separating the star and the arrow, the aviation plug inputs electric energy to electrify the memory alloy wire to contract and drive the pull pin to move, as shown in figure 3. Specifically, when the memory alloy wire contracts due to electrification, the fixing seat is pulled to move, the fixing seat drives the pulling pin to contract towards the inside of the outer barrel of the actuator, and therefore the separating mechanism limited by the pulling pin to move is released to generate response action, star-arrow separation is achieved, the action is reliable, and no impact exists. All the motion mechanisms are positioned in the shell formed by the outer cylinder of the actuator and the tail end cover, and the production, assembly and disassembly are convenient.

The invention adopts a closed integrated design, has compact structure, high integration level, excellent stability during pin pulling action, good tolerance to complex electromagnetic environment, convenient use and maintenance, high unlocking speed and high working reliability. During working, on the premise of not changing the separation safety, not reducing the rigidity of the whole structure and not reducing the bearing capacity, the rapid separation of the star and the arrow is realized, and the impact range which can be adapted to the carrying load is met. The special design combined with multiple factors ensures the stability of the separating action of the actuator fundamentally, and starting from a certain point or a certain angle, the impact cannot be eliminated, the impact source is difficult to distinguish, and the cause of the unstable factor cannot be distinguished, so the design of the actuator achieves a breakthrough result.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the invention, so that any modifications, equivalents, improvements and the like, which are within the spirit and principle of the present invention, should be included in the scope of the present invention.