Rescue satellite hose compact release device

Abstract

The present application relates to the technical field of manned spaceflight, and particularly relates to a rescue satellite hose compression release device, wherein the rescue satellite hose compression release device comprises a base and a strap; the base is formed with a containing groove and an avoiding groove; the base is suitable for detachable connection with a cabin plate of a rescue satellite; the strap is installed on the base and is suitable for restraining a hose in the containing groove; before launching the rescue satellite, the base is installed on the cabin plate of the rescue satellite, the hose is placed in the containing groove, and the hose is compressed in the containing groove by using the strap to cope with the violent impact and vibration during launching; after orbiting, the strap can be cut by using a cutting tool so that the hose is released and separated from the base. Compared with a traditional compression release device, the structure is simplified, the possibility of failure of a hose fixing and releasing compression release system is greatly reduced, the reliability of the hose fixing and releasing compression release system is improved, and the reliability of the whole satellite system is finally improved.

Description

Technical Field

[0001] This invention relates to the field of manned spaceflight technology, and in particular to a rescue satellite hose compression and release device. Background Technology

[0002] According to the rescue satellite mission plan, when a malfunctioning satellite requires repair, the rescue satellite will dock with or accompany it. Then, a robotic arm will grasp a flexible hose from the rescue satellite and connect it to the malfunctioning satellite. The hose must be securely clamped to the rescue satellite during launch to withstand the severe impact and vibration. After entering orbit, the hose will be released and detached from the rescue satellite.

[0003] Traditional compression and release devices on satellites are typically pyrotechnic compression and release devices, which use bolts to compress a flexible hose. These devices contain explosives and are connected by cables. An electrical signal ignites the explosives, causing a cutter to sever the connecting bolts and release the hose. Electrical detonation requires the installation of corresponding cables and activation circuits. For rescue satellites already equipped with robotic arms and cutting tools, these features undoubtedly increase the complexity of the hose compression and release device, increase the probability of malfunction, reduce the reliability of the device, and ultimately lower the reliability of the entire satellite system.

[0004] Therefore, how to improve the reliability of hose compression release devices has become a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] This invention provides a rescue satellite hose compression release device to solve the problem of how to improve the reliability of hose compression release devices.

[0006] On one hand, the present invention provides a rescue satellite hose compression release device, comprising:

[0007] The base has a receiving groove for accommodating the hose and a clearance groove for avoiding shearing tools; the base is suitable for detachable connection with the hatch of a rescue satellite;

[0008] Cable ties, mounted on the base, are used to restrain hoses within the receiving slot;

[0009] The base, cable ties, and hose are inserted into orbit along with the rescue satellite; the cable ties can be cut with a cutting tool to detach the hose from the base.

[0010] In some embodiments, the receiving groove is a single, upward-sloping, semi-circular opening located on one side of the base.

[0011] In some embodiments, a support column is provided on the other side of the base;

[0012] The clearance groove is formed between the support column and the receiving groove;

[0013] One end of the cable tie has a cable tie head, and the other end passes through the bottom of the base, the top of the receiving groove, the top of the clearance groove and the top of the support column in sequence before passing through the cable tie head.

[0014] In some embodiments, the top of the support column is provided with a clearance hole for the cable tie to pass through;

[0015] The base has a clearance passage at the bottom.

[0016] In some embodiments, there are two receiving slots, with their openings angled upwards and semi-circular in shape, located on opposite sides of the base.

[0017] In some embodiments, the clearance groove is formed between two receiving grooves;

[0018] One end of the cable tie is provided with a cable tie head, and the other end passes through the bottom of the base, the top of one of the receiving slots, the top of the clearance slot and the top of the other receiving slot in sequence, and then passes through the cable tie head.

[0019] In some embodiments, the bottom of the base is provided with a clearance passage.

[0020] In some embodiments, mounting holes are provided on opposite sides of the bottom of the base;

[0021] The cable ties are made of nylon.

[0022] The beneficial effects of this invention are as follows: The rescue satellite hose compression and release device of this invention features a base with a receiving groove for accommodating the hose and a clearance groove for avoiding shearing tools. Before launching the rescue satellite, the base is installed on the rescue satellite's cabin panel, and the hose is placed in the receiving groove. Cable ties are then used to compress the hose within the receiving groove to withstand the severe impact and vibration during launch. Afterward, the base, cable ties, and hose are inserted into orbit with the rescue satellite. Once in orbit, the clearance groove on the base allows the cable ties to be cut with a shearing tool, enabling the hose to detach from the base. Compared to traditional compression and release devices on satellites, this invention eliminates the need for detonation cables and excitation circuits, simplifies the structure, significantly reduces the likelihood of hose compression and release system failure, and improves the reliability of the system. Furthermore, it eliminates the need for assembling and installing explosives, avoiding the potential risks associated with explosive installation and storage. Attached Figure Description

[0023] Figure 1 These are front views of some specific embodiments of a rescue satellite hose compression and release device according to the present invention;

[0024] Figure 2 yes Figure 1Left view of the rescue satellite hose compression release device shown;

[0025] Figure 3 yes Figure 1 A top view of the rescue satellite hose compression release device shown;

[0026] Figure 4 yes Figure 1 The diagram shows the structure of the rescue satellite hose compression release device in use.

[0027] Figure 5 yes Figure 4 A sectional view;

[0028] Figure 6 yes Figure 4 The diagram shown illustrates the release of the rescue satellite hose clamping release device when it releases the hose.

[0029] Figure 7 This is a front view of some other specific embodiments of the rescue satellite hose compression and release device of the present invention;

[0030] Figure 8 yes Figure 7 Left view of the rescue satellite hose compression release device shown;

[0031] Figure 9 yes Figure 7 A top view of the rescue satellite hose compression release device shown;

[0032] Figure 10 yes Figure 7 The diagram shows the structure of the rescue satellite hose compression release device in use.

[0033] Figure 11 yes Figure 10 A sectional view;

[0034] Figure 12 yes Figure 7 The diagram shows the rescue satellite hose compression release device releasing the hose.

[0035] In the attached diagram, 100 is the rescue satellite hose compression and release device; 110 is the base; 111 is the receiving groove; 112 is the clearance groove; 113 is the support column; 1131 is the clearance hole; 114 is the clearance passage; 115 is the weight reduction hole; 120 is the cable tie; 121 is the cable tie head; 130 is the connector; 200 is the hose; 300 is the hatch plate; and 400 is the cutting tool. Detailed Implementation

[0036] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0037] As described in the background section, traditional clamping and release devices on satellites are typically pyrotechnic clamping and release devices, which use bolts to clamp the hose. These devices contain explosives and are connected by cables. An electrical signal ignites the explosives, causing a cutter to sever the connecting bolts and release the hose. Electrical detonation requires the installation of corresponding cables and ignition circuits. For rescue satellites already equipped with robotic arms and cutting tools, these features undoubtedly increase the complexity of the hose clamping and release system, increase the probability of malfunctions, reduce the reliability of the hose clamping and release system, and ultimately lower the reliability of the entire satellite system.

[0038] To solve the above problems, refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 6 , Figure 7 , Figure 8 , Figure 9 , Figure 10 , Figure 11 and Figure 12On one hand, the present invention provides a rescue satellite hose compression and release device 100, including a base 110 and a cable tie 120. The base 110 has a receiving groove 111 for accommodating a hose 200 and a clearance groove 112 for avoiding a shearing tool 400. The base 110 is suitable for detachable connection with a hatch 300 of a rescue satellite. The cable tie 120 is mounted on the base 110 and is suitable for restraining the hose 200 within the receiving groove 111. It should be noted that the hose 200 may contain rescue cables or the like, and its cross-section is not necessarily a regular circle. The cable tie 120 has a certain degree of flexibility, allowing it to be bent and tightly adhered to the outer wall of the hose 200 along its circumference, thereby compressing the hose 200 within the receiving groove 111. Before launching the rescue satellite, the base 110 is installed on the rescue satellite's cabin panel 300, and the hose 200 is placed in the receiving slot 111. Cable ties 120 are then used to secure the hose 200 within the receiving slot 111 to withstand the severe impact and vibration during launch. Afterward, the base 110, cable ties 120, and hose 200 are inserted into orbit with the rescue satellite. Once in orbit, the base 110 has a clearance groove 112 to allow the shearing tool 400 to pass, enabling the cable ties 120 to be cut and the hose 200 to detach from the base 110. Compared to traditional compression and release devices on satellites, this eliminates the need for detonation cables and excitation circuits, resulting in a simpler structure and significantly reducing the likelihood of hose compression and release system failure, thus improving its reliability. Furthermore, the elimination of the need for explosives installation avoids the potential risks associated with explosives storage, ultimately enhancing the overall reliability of the satellite system.

[0039] Preferably, the base 110 is made of non-metallic materials such as polyimide, and the cable tie 120 is made of nylon. Compared with the traditional compression and release system that uses metal materials, the overall weight is lighter, which is beneficial to increasing the effective payload and saving rescue satellite fuel.

[0040] In some of these embodiments, such as Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6As shown, there is one receiving groove 111 with an upward-sloping opening, located on the top of one side of the base 110. The opening is semi-circular, which not only facilitates the insertion and removal of the hose but also provides a certain degree of tolerance and adaptability to deviations in the actual diameter of the hose. A support post 113 is provided on the top of the other side of the base 110. A clearance groove 112 is formed between the support post 113 and the receiving groove 111. One end of the cable tie 120 is provided with a cable tie 120 head, and the other end passes sequentially around the bottom of the base 110, the top of the receiving groove 111, the top of the clearance groove 112, and the top of the support post 113 before passing through the cable tie 120 head. When the hose 200 is fixed to the base 110, the cross-section of the hose 200 will deform. On the one hand, the opening of the receiving groove 111 is set to be obliquely upward; on the other hand, the receiving groove 111 has a semi-circular structure, which facilitates a better fit between the cable tie 120 and the receiving groove 111. Before the hose 200 is put into orbit with the rescue satellite, its position can be better constrained. A clearance hole 1131 for the cable tie 120 to pass through is provided at the top of the support column 113. A clearance channel 114 is provided at the bottom of the base 110. The clearance hole 1131 and the clearance channel 114 can effectively prevent the cable tie 120 from moving relative to the base 110 and prevent the cable tie 120 from detaching from the base 110, thereby ensuring the fixing effect of the hose 200.

[0041] In other embodiments, such as Figure 7 , Figure 8 , Figure 9 , Figure 10 , Figure 11 and Figure 12 As shown, there are two receiving slots 111, with their openings angled upwards, located on the top of opposite sides of the base 110. The openings are semi-circular, which not only facilitates the insertion and removal of the hose but also provides a certain degree of tolerance and adaptability to deviations in the actual diameter of the hose. A clearance slot 112 is formed between the two receiving slots 111. One end of the cable tie 120 is provided with a cable tie 120 head, and the other end passes sequentially around the bottom of the base 110, the top of one of the receiving slots 111, the top of the clearance slot 112, and the top of the other receiving slot 111 before passing through the cable tie 120 head. When the two hoses 200 are fixed to the base 110, their cross-sections deform. Firstly, the openings of the two receiving slots 111 are angled upwards. Secondly, the semi-circular structure of both receiving slots 111 facilitates a better fit between the cable tie 120 and the two receiving slots 111, effectively restraining the position of the two hoses 200 before they enter orbit with the rescue satellite. An obstacle avoidance channel 114 is provided at the bottom of the base 110. The obstacle avoidance channel 114 effectively prevents the cable tie 120 from moving relative to the base 110, preventing it from detaching from the base 110, thus ensuring the effective fixation of the hoses 200.

[0042] Specifically, in the exemplary example, a mounting hole is provided on each of the opposite sides of the bottom of the base 110. Correspondingly, two mounting holes are provided on the rescue satellite's panel 300. The base 110 can be fixed to the rescue satellite's panel 300 through the two mounting holes using two connectors 130.

[0043] Preferably, the mounting hole is a threaded hole, and correspondingly, the connector 130 is a bolt. The mounting hole can also be a insertion hole, and correspondingly, the connector 130 is a pin.

[0044] Preferably, a plurality of weight-reducing holes 115 are provided on the base 110 to reduce the weight of the base 110, which is beneficial to increasing the effective payload and saving rescue satellite fuel.

[0045] On the other hand, a rescue satellite hose compression and release system includes a rescue satellite, a hose 200, a cutting tool 400, and a rescue satellite hose compression and release device 100 provided in any of the above embodiments. A base 110 is detachably connected to the rescue satellite's cabin 300 via a connector 130. The hose 200 is disposed within a receiving groove 111 of the base 110. The cutting tool 400 is used to cut the cable ties 120. Before launching the rescue satellite, the base 110 is installed on the rescue satellite's cabin 300, and the hose 200 is placed in the receiving groove 111. The cable ties 120 are then used to compress the hose 200 within the receiving groove 111 to withstand the severe impact and vibration during launch. Afterward, the base 110, cable ties 120, and hose 200 are inserted into orbit along with the rescue satellite. After entering orbit, the shearing tool 400 is prevented from passing through the avoidance groove 112 formed on the base 110, allowing the cable tie 120 to be cut by the shearing tool 400, thus enabling the hose 200 to detach from the base 110. Compared to traditional compression and release devices on satellites, there is no need to install detonation cables and excitation circuits, and the structure is also much simpler, greatly reducing the possibility of hose compression and release system failure and improving the reliability of the hose compression and release system. Furthermore, the elimination of the need to assemble and install explosives avoids the potential risks associated with explosives installation and storage, ultimately improving the reliability of the entire satellite system.

[0046] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0047] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0048] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0049] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0050] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A rescue satellite hose pinching release device, characterized by, The utility model relates to a base for accommodating a hose and avoiding a cutting tool, a cable tie installed on the base for restraining the hose in the accommodating groove, and the base, the cable tie and the hose being separated from the base by cutting the cable tie with the cutting tool after the rescue satellite is launched into orbit. The base is detachably connected with a deck of the rescue satellite. The base, the cable tie and the hose are separated from the base by cutting the cable tie with the cutting tool after the rescue satellite is launched into orbit. The accommodating groove is formed on one side of the base. The other side of the base is provided with a support column. The avoiding groove is formed between the support column and the accommodating groove. One end of the cable tie is provided with a cable tie head, and the other end of the cable tie passes through the cable tie head after passing through the bottom of the base, the top of the accommodating groove, the top of the avoiding groove and the top of the support column in sequence. Or, the accommodating groove is formed on the opposite sides of the base. The avoiding groove is formed between the two accommodating grooves. One end of the cable tie is provided with a cable tie head, and the other end of the cable tie passes through the cable tie head after passing through the bottom of the base, the top of one of the accommodating grooves, the top of the avoiding groove and the top of the other accommodating groove in sequence. The cable tie has a certain flexibility, can be bent and closely attached to the outer wall of the hose along the circumference of the hose to press the hose in the accommodating groove. Before launching the rescue satellite, the base is installed on the deck of the rescue satellite, the hose is placed in the accommodating groove, and the hose is pressed in the accommodating groove by the cable tie to cope with the severe impact and vibration during launching. After being launched into orbit, the hose is separated from the base by cutting the cable tie with the cutting tool. The bottom of the base is provided with an avoiding channel.

2. The rescue satellite hose pinching release device of claim 1, wherein, When the accommodating groove is one, the top of the support column is provided with an avoiding hole for the cable tie to pass through.

3. The rescue satellite hose pinching release device of claim 2, wherein, The bottom of the base is provided with mounting holes on the opposite sides.

4. A rescue satellite hose pinching release device according to any of claims 1-3, characterized in that, The material of the cable tie is nylon. ​

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