阅读说明：本技术 航天器适配分离架及包括该分离架的适配分离装置 (Spacecraft adaptive separation frame and adaptive separation device comprising same ) 是由 李志军 武练梅 于 2019-11-08 设计创作，主要内容包括：本发明公开一种航天器适配分离架及包括该分离架的适配分离装置,分离架包括底座,以及位于底座上的且沿底座周向方向均匀设置的至少两个单元架体；单元架体包括位于底座上方的顶壁板,以及侧壁板；顶壁板的顶面形成安装航天器的载荷安装面,载荷安装面的法线与分离架正X方向形成夹角θ；顶壁板上包括至少三个分离弹簧推杆孔以及至少三个爆炸螺栓孔。本发明适用于多航天器分离架使用,多航天器仅通过一次装配即可安装于由分离架顶壁板的顶面所形成的用于安装航天器的载荷安装面上,有利于保证多个航天器之间的相对位置精度,占用空间更小及刚度更容易保证。(The invention discloses a spacecraft adaptive separation frame and an adaptive separation device comprising the same, wherein the separation frame comprises a base and at least two unit frame bodies which are positioned on the base and are uniformly arranged along the circumferential direction of the base; the unit frame body comprises a top wall plate and a side wall plate, wherein the top wall plate is positioned above the base; a load mounting surface for mounting the spacecraft is formed on the top surface of the top wall plate, and an included angle theta is formed between the normal of the load mounting surface and the positive X direction of the separation frame; the top wall plate comprises at least three separated spring push rod holes and at least three explosion bolt holes. The invention is suitable for a multi-spacecraft separation frame, and the multi-spacecraft can be arranged on a load mounting surface for mounting the spacecraft, which is formed by the top surface of the top wall plate of the separation frame, only by one-time assembly, so that the relative position precision among the plurality of spacecrafts is ensured, the occupied space is smaller, and the rigidity is easier to ensure.)

1. A spacecraft adaptive separation frame is characterized by comprising a base and at least two unit frame bodies, wherein the at least two unit frame bodies are positioned on the base and are uniformly arranged along the circumferential direction of the base;

the unit frame body comprises a side wall plate integrally extending upwards from the base and a top wall plate integrally extending transversely from the top of one end, far away from the base, of the side wall plate; the top surface of the top wall plate forms a load mounting surface for mounting the spacecraft, and an included angle theta is formed between the normal of the load mounting surface and the positive X direction of the separation frame;

the top wall panel includes thereon:

at least three separated spring push rod holes which are uniformly arranged along the circumferential direction of the top wall plate and penetrate through the two side surfaces of the top wall plate; and

at least three explosion bolt holes which are uniformly arranged along the circumferential direction of the top wall plate and penetrate through the two side surfaces of the top wall plate.

2. A spacecraft adaptive separation rack according to claim 1, wherein the separation rack is a one-piece structure formed by casting.

3. A spacecraft adaptive separation rack according to claim 1, wherein adjacent two unit rack bodies include a common side wall plate.

4. The spacecraft adaptive separation rack of claim 1, wherein the top wall plate comprises a plurality of guide pins and a plurality of positioning pins arranged along the circumferential direction of the top wall plate on the upper plate surface;

the guide pin is configured to guide separation of the spacecraft from the separation frame;

the locating pins are configured to locate the installation of the spacecraft on the spacer top wall panel.

5. A spacecraft adaptive separation rack according to claim 1, wherein the separation spring push rod holes alternate with explosion bolt holes at equal intervals.

6. A spacecraft adaptive splitter frame according to claim 1, wherein the base includes an edge portion at an edge position and a mounting portion inboard of the edge portion.

7. A spacecraft adaptive separation rack according to claim 1, wherein the side wall plate includes access openings extending through both side surfaces of the side wall plate.

8. A spacecraft adaptive separation apparatus, wherein the separation apparatus comprises a separation frame according to any one of claims 1 to 7;

the separating device also comprises a separating spring assembly and a separating initiating explosive device which are combined and fixed on the separating frame.

9. A spacecraft adaptive separation device according to claim 8, wherein the separation spring assembly comprises at least:

a spring housing formed on the top wall plate;

a split spring push rod located within the spring housing; and

a separation spring in a pre-pressed state;

the acting force direction of the separation spring is along the axial direction of the separation spring push rod; the separation spring is configured to eject the rod end of the separation spring push rod out of the separation spring push rod hole.

10. A spacecraft adaptive separation device according to claim 8, wherein the pyrotechnic device comprises at least:

an initiator fixed on the base in a combined manner;

explosive bolts for fixing the spacecraft; and

an electrically non-conductive detonation assembly for connecting the detonator to the detonation bolt;

the explosive bolt comprises a connecting part extending from the explosive bolt hole to the outside of the top surface of the top wall plate.

Technical Field

The invention relates to the technical field of aerospace craft. And more particularly, to a spacecraft adaptive separation frame and an adaptive separation device including the same.

Background

The adaptive separation device is an important component of a space product and plays a role in connecting and separating a spacecraft from a carrier at a launching section. In the ascending section of the carrier, the adaptive separation device connects the spacecraft with the carrier so as to bear the overload in the launching process; when the spacecraft is transported by the carrier to the specified orbit and state, the adaptive separation device releases the connection of the spacecraft and the carrier and separates the spacecraft out at a certain speed. In order to save on launch costs, there is often a need for an adaptive separation device capable of carrying a plurality of spacecraft. Usually, the adaptive separation device and the spacecraft are mounted inside the fairing, with strict requirements on the size of the space.

In the conventional structure of the multi-spacecraft adaptive separation device, each spacecraft is provided with an adaptive separation device, and the adaptive separation device of each spacecraft is installed on a carrier through a support. Each set of adaptive separation device generally comprises a set of separation initiating system, a separation mechanism and a support frame body. The scheme has the characteristics that the adaptive separation device is convenient to connect with the spacecraft, the adaptive separation device is easy to universalize, the cost is reduced, but some problems exist, and the adaptive separation device mainly needs some connecting structures such as connecting flanges, screws and the like when being installed on a main structure, so that the structural quality of the carrier is improved, and meanwhile, a certain operation space is needed during connection operation, the layout is not compact enough, and the space occupied by a fairing is larger. In addition, in the above adaptive separation device, the installation of the spacecraft and the adaptive separator constitutes a first assembly, the installation of the adaptive separator and the support frame constitutes a second assembly, and the support frame constitutes a third assembly when being installed on the carrier, so that the relative installation position accuracy between a plurality of spacecrafts cannot be ensured due to the multiple independent installation of each spacecraft, and the adaptive separation device cannot be applied to places with higher relative position accuracy requirements between the spacecrafts, and the multiple assembly of the adaptive separation device is not favorable for the rigidity requirement of the fixed state of the spacecraft and the carrier.

Disclosure of Invention

In view of the above problems, an object of the present invention is to provide a spacecraft adaptive separation frame to solve the problems that the accuracy of the installation position is not high, and the safe distance and the separation direction between each spacecraft are prone to error during the installation process of the existing multi-spacecraft.

Another object of the present invention is to provide an adaptive separating apparatus comprising the above adaptive separating frame. The adaptive separation device can be used as an independent component for production and manufacturing, can accommodate and mount a plurality of spacecrafts simultaneously, simplifies the mounting step of the spacecrafts in the fairing of the carrier, and improves the relative precision of the mounting positions of the spacecrafts.

In order to achieve the purpose, the invention adopts the following technical scheme:

according to one object of the invention, the invention provides a spacecraft adaptive separation frame, which comprises a base and at least two unit frame bodies, wherein the at least two unit frame bodies are positioned on the base and are uniformly arranged along the circumferential direction of the base;

the unit frame body comprises a side wall plate integrally extending upwards from the base and a top wall plate integrally extending transversely from the top of one end, far away from the base, of the side wall plate; the top surface of the top wall plate forms a load mounting surface for mounting the spacecraft, and an included angle theta is formed between the normal of the load mounting surface and the positive X direction of the separation frame;

the top wall panel includes thereon:

at least three separated spring push rod holes which are uniformly arranged along the circumferential direction of the top wall plate and penetrate through the two side surfaces of the top wall plate; and

at least three explosion bolt holes which are uniformly arranged along the circumferential direction of the top wall plate and penetrate through the two side surfaces of the top wall plate.

Furthermore, it is preferable that the separation frame is a unitary structure formed by casting.

In addition, it is preferable that adjacent two unit frame bodies include a common sidewall plate.

In addition, preferably, the upper plate surface of the top wall plate comprises a plurality of guide pins and a plurality of positioning pins which are arranged along the circumferential direction of the top wall plate;

the guide pin is configured to guide separation of the spacecraft from the separation frame;

the locating pins are configured to locate the installation of the spacecraft on the spacer top wall panel.

Furthermore, it is preferable that the separation spring push rod holes and the explosion bolt holes are alternately arranged at equal intervals.

Further, it is preferable that the base includes an edge portion at an edge position and a mounting portion inside the edge portion.

In addition, it is preferable that the side wall plate includes an operation opening penetrating both side surfaces of the side wall plate.

According to another object of the present invention, there is also provided an adaptable separating device comprising a separating frame as described above;

the separating device also comprises a separating spring assembly and a separating initiating explosive device which are combined and fixed on the separating frame.

Furthermore, it is preferable that the separation spring assembly includes at least:

a spring housing formed on the top wall plate;

a split spring push rod located within the spring housing; and

a separation spring in a pre-pressed state;

the acting force direction of the separation spring is along the axial direction of the separation spring push rod; the separation spring is configured to eject the rod end of the separation spring push rod out of the separation spring push rod hole.

Furthermore, it is preferable that the pyrotechnic device includes at least:

an initiator fixedly combined with the base;

explosive bolts for fixing the spacecraft; and

an electrically non-conductive detonation assembly for connecting the detonator to the detonation bolt;

the explosive bolt comprises a connecting part extending from the explosive bolt hole to the outside of the top surface of the top wall plate.

The invention has the following beneficial effects:

compared with the prior art, the invention firstly provides the spacecraft adaptive separation frame which is of an integral structure and is suitable for the multi-spacecraft separation frame, the separation spring assembly and the separation initiating device can be arranged on the separation frame in advance, the multi-spacecraft can be arranged on a load installation surface which is formed by the top surface of the top wall plate of the separation frame and is used for installing the spacecraft only through one-time assembly, the plurality of spacecrafts are arranged on the integral separation frame, the relative position precision among the plurality of spacecrafts is favorably ensured, the installation of each spacecraft is more compact, the occupied space of a fairing is less, and the rigidity of the separation frame is also more easily ensured. In addition, the problem that the safe distance and the separation direction between the spacecrafts are easy to have errors can be avoided.

In addition, the side wall plate on the separation frame provided by the invention can be used for installing photoelectric equipment or accurate measurement equipment which can improve the high-precision requirement of spacecraft separation, such as an imager, a reference mirror and the like, and the photoelectric equipment or the accurate measurement equipment can be used for detecting the relative position between the spacecrafts so as to improve the installation precision of the spacecrafts.

According to another aspect of the invention, the adaptive separation device comprising the separation frame, provided by the invention, can integrate the separation spring assembly of the separation frame and the separation initiating explosive device into an integral structure, so that the installation of multiple spacecrafts is facilitated, the situation that the relative installation position precision among the multiple spacecrafts cannot be ensured because each spacecraft is independently installed in the fairing of the carrier respectively, errors are easy to occur in the safe distance and the separation direction among the spacecrafts, and various problems and hidden dangers are brought to the release and separation of the spacecrafts is avoided.

Drawings

The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.

Fig. 1 shows one of the structural schematic diagrams of the adaptive separation frame provided by the present invention.

Fig. 2 shows a second schematic structural diagram of the adaptive separation frame provided by the present invention.

Fig. 3 shows a schematic perspective view of an adaptive separating device provided by the present invention.

Fig. 4 is a schematic top view of an adaptive separating apparatus provided by the present invention.

Fig. 5 is a schematic side view of an adaptive separating device provided by the invention.

Fig. 6 shows a schematic diagram of a separation spring assembly in an adaptive separation device provided by the present invention.

Detailed Description

Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that: the relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise.

The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses.

Techniques and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be considered a part of the specification where appropriate.

In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

In order to solve the defects of the prior art, according to one aspect of the present invention, the present invention provides a spacecraft adaptive separation frame, and specifically, as shown in fig. 1 and fig. 2, in one embodiment of the present invention, the separation frame 1 includes a base 11, and at least two unit frame bodies located on the base 11 and uniformly arranged along a circumferential direction of the base 11;

the unit frame body comprises a side wall plate 13 integrally extending upwards from a base 11 and a top wall plate 12 integrally extending transversely from the top of one end, far away from the base 11, of the side wall plate 13; the top surface of the top wall plate 12 forms a load mounting surface 10 for mounting the spacecraft, and the normal of the load mounting surface 10 forms an included angle theta with the positive X direction of the separation frame; the angle theta is generally 0 deg. to 45 deg., preferably said angle theta is 3.5 deg..

In the structure of the separation frame provided by the present invention, the top wall plate 12 includes:

at least three separate spring push rod holes 121 uniformly arranged along the circumferential direction of the top wall plate 12 and penetrating through the two side surfaces of the top wall plate 12; and at least three explosion bolt holes 122 uniformly arranged along the circumferential direction of the top wall plate 12 and penetrating through both side surfaces of the top wall plate 12. In one embodiment, referring to fig. 1, three separate spring push rod holes 121 alternate with three explosion bolt holes 122 at equal intervals, i.e., the distance between any explosion bolt hole 122 and the adjacent separate spring push rod hole 121 is equal. The installation structure has the advantages that the explosive bolt holes 122 and the separation spring push rod holes 121 are alternately and uniformly arranged at intervals, and the explosive bolts arranged in the explosive bolt holes can provide stable installation acting force for the spacecraft when the spacecraft is installed, so that the spacecraft can be completely attached and fixed to a load installation surface formed by the top surface of the top wall plate and used for installing the spacecraft. The separation spring push rod arranged in the separation spring push rod hole can provide stable thrust for the spacecraft when the spacecraft is released and separated, and the arrangement mode of the separation spring push rod and the separation spring push rod can prevent mutual interference between the explosion bolt and the separation spring push rod when the spacecraft is released and separated, so that the spacecraft is released and separated in an error direction.

Compared with the existing adaptive separation device designed for each spacecraft; the invention provides a spacecraft adaptive separation frame 1 which is an integrated structure formed by casting, and can be suitable for a separation frame for mounting multiple spacecrafts, wherein a separation spring assembly and a separation initiating device are mounted on the separation frame in advance to form an integrated structure separation device, the multiple spacecrafts can be mounted on a load mounting surface formed by the top surface of a top wall plate of the separation frame and used for mounting the spacecrafts only through one-time assembly, the multiple spacecrafts are mounted on the integrated separation frame, the relative position precision among the multiple spacecrafts is favorably ensured, the installation of each spacecraft is more compact, the occupied space of a fairing is less, the rigidity of the separation frame is easier to ensure, and in addition, the problem that the safety distance among the spacecrafts and the separation direction are easy to generate errors can be avoided. The side wall plate on the separation frame can be provided with photoelectric equipment or accurate measurement equipment which can improve the high-precision separation requirement of the spacecrafts, and the photoelectric equipment or the accurate measurement equipment can be used for detecting the relative position of each spacecraft so as to improve the installation precision of each spacecraft.

In one embodiment, the space enclosed between the top wall panel 12 and the side wall panel 13 preferably forms a mounting chamber, in order to be suitable for mounting other electronic components of a spacecraft or separation equipment. In order to reduce the cross-sectional volume of the separation frame as much as possible and not occupy additional space in the fairing of the vehicle under the condition of ensuring that the safety distance between the multiple spacecrafts is sufficient, preferably, as shown in the figure, two adjacent unit frame bodies comprise a common side wall plate 13.

In one embodiment, as shown in fig. 3 or fig. 5, preferably, the top wall plate 12 includes a plurality of guide pins 123 and a plurality of positioning pins 124 on the upper plate surface thereof, which are arranged along the circumferential direction of the top wall plate 12;

the guide pins 123 are configured to guide the separation of the spacecraft from the separation frame 1;

the locating pins 124 are configured to locate the spacecraft to be mounted on the top wall plate 12 of the spacer 1.

In one embodiment, as shown in fig. 1 and 2, the base 11 includes an edge portion 111 at an edge position and a mounting portion 112 located inside the edge portion 111. The edge portion 111 is configured for mounting and securing the splitter frame 1 within the vehicle fairing; the mounting portion 112 is configured for mounting various types of devices, such as an initiator holder for holding an initiator in a discrete pyrotechnic device, and various types of sensors or electronics, as the present invention is not limited in this respect.

In addition, in the separation frame structure provided by the present invention, the side wall plate 13 further includes an operation opening 131 penetrating through both side surfaces of the side wall plate 13. The operation opening 131 reserves an operation space for installing the separation initiating explosive device on the separation frame body, and the installation of the separation initiating explosive device is convenient.

According to another aspect of the invention, the invention also provides a spacecraft adaptive separation device, which is shown in combination with fig. 3 to 6, and comprises a separation frame 1, a separation spring assembly 2 and a separation firer device 3, wherein the separation spring assembly is fixedly combined on the separation frame 1. This adaptation separator can integrate release bracket 1, separation spring assembly 2 and separation priming system device 3 become an overall structure, the installation of the many spacecrafts of being convenient for, avoided each spacecraft to install alone respectively to the delivery vehicle radome, can't guarantee the problem that relative mounted position precision occupation space between a plurality of spacecrafts is bigger and rigidity is more difficult to guarantee, and the safe distance and the separation direction of having still avoided between each spacecraft easily appear the error, the condition that brings many problems hidden danger for the release separation of spacecraft takes place.

In a particular embodiment, preferably, as shown in connection with fig. 5, the separation spring assembly 2 comprises at least:

a spring housing 21 formed on the top wall plate 12 within the mounting chamber; the spring housing 21 may be integrally formed by the separate frame 1;

a separate spring push rod 22 located within the spring housing 21; and

a separation spring 23 in a pre-pressed state;

the acting force direction of the separation spring 23 is along the axial direction of the separation spring push rod 22; the separation spring 23 is configured to eject the rod end 221 of the separation spring pusher 22 out of the separation spring pusher bore 121. The rod end 221 of the release spring pusher 22 provides a force to release the separation of the spacecraft mounted on the load mounting surface 10 from the separation frame 1.

In a specific embodiment, as shown in fig. 3 to 5, the pyrotechnic device 3 at least includes:

an initiator 31 fixed on the base 11; specifically, the initiator 31 is fixedly mounted on the mounting portion 112 of the base 11;

explosive bolts 32 located in the installation chamber to fix the spacecraft; and

an electrically non-conductive detonation assembly 33 for connecting the initiator 31 to the detonation bolt 32;

the explosion bolt 32 includes a connecting portion 321 extending from the explosion bolt hole 122 to outside the top surface of the top wall plate 12. The connecting portion 321 is used for connection with a spacecraft mounted on the load mount surface 10 formed by the top surface of the top wall plate 12. It will be appreciated by those skilled in the art that the non-electric detonating assembly 33 will typically include a manifold, an output connector, and a restraining detonating cord, and the invention is not limited in detail herein.

Referring to fig. 1 to 5, the adaptive separation frame 1 of the present invention has a circular disk structure, and has three load mounting surfaces 10 formed by the top surfaces of top wall plates 12 at the front side (+ X direction), and preferably, the normal line of each load mounting surface 10 forms an angle of 3.5 ° with the + X direction of the separation frame. In a specific embodiment, three separation spring assemblies 2, three separation firer devices 3, two positioning pins 124 and four guiding pins 123 are arranged on each load mounting surface 10, wherein three separation spring assemblies 2 provide power for the separation of the spacecraft, three separation firer devices 3 are used for connecting, fixing and releasing separation between the spacecraft and the adaptive separation frame 1, two positioning pins 124 are used for mechanical positioning of the spacecraft and the adaptive separation frame 1, and four guiding pins 123 are used for guiding the spacecraft in the releasing separation process. The side wall plate 13 of the adaptive separation frame 1 at the periphery of each load mounting surface 10 comprises three operation ports 131, and the operation ports 131 can be used for mounting operation when the explosive bolts 32 are connected; the side wall plate 13 on the side of each load mounting surface 10 and the area between two adjacent load mounting surfaces 10 can be used for mounting equipment, especially equipment with high requirements on mounting accuracy, such as an imager, a reference mirror and the like. The back of the adaptive separation frame is of a cavity structure, so that the adaptive separation frame is of an open structure and is convenient to process and produce. The adaptive separating frame can be made of cast aluminum alloy materials and is formed in a mode of casting and machining.

As shown in connection with fig. 4-6, there are three sets of split spring assemblies 2 per load mounting surface 10. Each separation spring assembly 2 comprises a spring housing 21, a separation spring push rod 22, a separation spring 23, a spring baffle 24 and a spring positioning column 25. The release spring 23 is in a compressed state before the spacecraft is released, and applies a predetermined thrust to the spacecraft. During assembly, the release spring 23 is first tensioned by a process tension rod 4, and the process tension rod 4 can be arranged on the rear side of the adapter release bracket 1. The process pull rod 4 is connected to the separation spring push rod 22 through threads, then is installed on the spring positioning column 25 through the gasket 5, and the process pull rod 4 is fixed through the nut 6 to play a role in preventing looseness. After the spacecraft is mounted on the load mounting surface 10, the nut 6, the gasket 5 and the process pull rod 4 are detached from the rear side of the adaptive separation frame 1, so that the separation spring push rod 22 directly acts on the spacecraft under the action of the separation spring 23. In order to make room for the installation of explosive bolts 32, the separation spring assembly 2 has a set of spring elements located near the center of the adapter spacer 1, which makes room for the installation of explosive bolts 32.

In the present invention, the separation pyrotechnic device 3 is used to attach and release a spacecraft as a load. In one embodiment, each separate set of pyrotechnic devices 3 includes a two shot initiator 31, a set of non-electrically conductive pyrotechnic assemblies 33, and a three shot bolt 32. The three explosion bolts 32 are respectively provided with an operation opening 131 formed in the side wall plate 13 in the vicinity thereof, and the operation openings 131 provide an operation space for installing the explosion bolts 32. Each explosion bolt 32 can be provided with a recovery cap 321, and the recovery cap 321 is used for recovering the bolt body after the explosion bolt 32 works, so that the bolt body of the explosion bolt 32 is prevented from swinging in a large range.

In one embodiment the process of installation of a spacecraft with the adaptive separation device provided by the present invention is: firstly, the separation spring assembly 2 is installed on the adaptive separation frame 1, the separation spring 23 is compressed through a tool, and the separation spring 23 is kept in a pressing state by the process pull rod 4 until the rod end part 221 of the separation spring push rod 22 does not protrude out of the load mounting surface 10. Then the guide pin 123, the positioning pin 124 and the separation firer device 3 are installed on the adaptive separation frame 1; then butting the spacecraft with the load mounting surface 10 on the adaptive separation frame 1, and fastening and separating the initiating explosive device 3 through the operation port 131; the process tension rod 4 of the separation spring assembly 2 is then released, causing the separation spring push rod 22 to act directly on the spacecraft under the force of the separation spring 23. The process of spacecraft separation is: the separation of the separation initiating explosive device 3 is realized by supplying power to the separation initiating explosive device 3, the connection between the spacecraft and the adaptation separation frame 1 is released, and the spacecraft moves relative to the adaptation separation frame 1 under the thrust action of the separation spring assembly 2, so that the release and the separation of the spacecraft are realized.

It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations and modifications can be made on the basis of the above description, and not exhaustive enumeration of all embodiments, and obvious variations and modifications can be made without departing from the scope of the present invention.