Manual exhaust sealing cover device for emergency of manned spacecraft

Abstract

The invention discloses a manual exhaust sealing cover device for emergency of a manned spacecraft, and belongs to the field of pressure control and pressure relief in cabins of manned spacecrafts. The device comprises a sealing cover, a wrench, a sealing valve body, a reed and a pin. The sealing cover is hinged to the sealing valve body through a pin, hot-pressing rubber is arranged on the lower surface of the sealing cover, and a sealing ring is arranged on the upper surface of the sealing valve body and matched with the hot-pressing rubber. The two wrenches are connected to the two sides of the sealing cover through pins, and the reeds are fixed to the inner sides of the wrenches. Under the non-emergency condition, the sealing cover is pressed after the two wrenches buckle the sealing valve body, the hot-pressing rubber is pressed on the sealing ring, and the reed provides sealing force. In emergency, an astronaut opens the wrench firstly when wearing clothes, then the sealing cover is lifted up for pressure relief, and it is guaranteed that the astronaut goes out of a cabin smoothly.

Description

Technical Field

[0001] The invention relates to a sealing cover device for manual exhaust in emergency of a manned spacecraft, belonging to the field of pressure control and pressure relief in a cabin of a manned spacecraft. Background Art

[0002] A certain type of manned spacecraft needs to control cabin pressure during the launch phase, and the gas in the cabin needs to be depressurized when leaving the cabin. When the upstream pressure relief valve fails, pressure relief cannot be performed, seriously affecting the astronauts' mission to leave the cabin. If a special pressure relief manual valve or electric valve (electric valves generally need to be used with a separate controller) is added to the pressure relief pipeline system, the space for the spacecraft as a whole will be tight and the weight will increase significantly, which does not meet the requirements of miniaturization and lightweight design.

[0003] In order to solve this problem, it is urgent to develop a sealing cover device that can perform manual exhaust and pressure relief operations in emergency situations, which can not only ensure sealing but also enable manual exhaust. At the same time, it is required to have a simple structure, light weight, easy operation and strong practicality. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a sealing cover device for manual emergency exhaust of a manned spacecraft, which serves as a redundant design of the manned spacecraft extravehicular pressure relief pipeline system, so as to enable astronauts to manually exhaust the cabin in an emergency and ensure the smooth progress of the astronauts' extravehicular mission.

[0005] The technical solution of the present invention is:

[0006] A sealing cover device for emergency manual exhaust of a manned spacecraft, comprising a sealing cover, a wrench, a sealing valve body, a reed, and a pin;

[0007] The sealing cover and the sealing valve body are hinged by pins, the lower surface of the sealing cover is provided with hot-pressed rubber, the upper surface of the sealing valve body is provided with a sealing ring, and the sealing ring cooperates with the hot-pressed rubber;

[0008] The two wrenches are connected to the two sides of the sealing cover through pins, and the spring is fixed inside the wrenches;

[0009] In non-emergency situations, the sealing cover is tightened after two wrenches are used to hold the sealing valve body, the hot-pressed rubber is pressed against the sealing ring, and the reed provides sealing force; in emergency situations, the astronauts wear the suit to open the wrench first, and then lift the sealing cover to release the pressure.

[0010] Furthermore, the sealing cover includes a sealing cover base and hot-pressed rubber; the hot-pressed rubber is bonded to the sealing cover base by a hot vulcanization process; wherein the hot-pressed rubber has two circles, adopts a double-pass bacterial seal, and the large circle is 0 to 0.02 mm higher than the small circle; when the sealing cover is closed, the gas in the cabin first passes through the large circle, and then passes through the small circle before flowing out of the cabin.

[0011] Furthermore, the sealing cover is provided with two evenly distributed limiting bosses to prevent the rubber from being damaged by overpressure or excessively deformed and affecting its service life.

[0012] Furthermore, the sealing valve body has two sealing rings, and ears are provided at both ends of the valve body. In non-emergency situations, the ears are held with a wrench to press the hot-pressed rubber onto the sealing ring; the lower surface of each ear has a four-sided limiting structure, the highest point of the four-sided limiting structure is an arc, with slopes of 45°~46° and 30°~31° on both sides, and an R0.5~0.6mm arc protrusion on the top.

[0013] Furthermore, there is a circular protrusion on the top of the reed. When the wrench is buckled on the support ear, the reed climbs a 30° slope and will be locked when it passes the highest point of the four-way limit structure.

[0014] Furthermore, when the wrench is opened, the circular protrusion of the reed climbs the 45° slope and is released after passing the highest point of the four-way limiting structure.

[0015] Furthermore, except for the hot-pressed rubber, all other materials in the sealing cover device are made of metal materials that are compatible with the Class I working fluid in the manned spacecraft.

[0016] Furthermore, it also includes a cap nut, and the pin connecting the sealing cover and the wrench is tightened by the cap nut.

[0017] Furthermore, the sealing cover is designed with an extended lever arm, which makes it easier for astronauts to open the sealing cover to release pressure while putting on their suits.

[0018] Furthermore, the wrench is designed to be semi-enclosed, and the edge of the reed is wrapped by the wrench, so that the astronauts will not touch the edge of the reed when manually operating the suit.

[0019] The advantages of the present invention compared with the prior art are:

[0020] (1) The sealing cover device for manual exhaust of manned spacecraft in emergency designed by the present invention can be flexibly installed and integrated. In order to facilitate astronauts to wear and operate the device, the weight and volume of the device are small, which can greatly reduce the weight and volume of the manned spacecraft pipeline system and is easy to operate.

[0021] (2) The present invention adopts a method in which closing the wrench can seal and opening the wrench can release pressure. The sealing adopts a double-pass bacteria seal, which is simple and convenient to operate, has reliable sealing and strong practicality.

[0022] (3) Except for the hot-pressed rubber, all other materials of the present invention are made of metal materials that are compatible with the working fluid of the manned spacecraft. This solves the compatibility problem with the working fluid of the manned spacecraft and prevents corrosion, aging, and excess materials.

[0023] (4) The reed used in the present invention has a circular protrusion, which cooperates with the four-way limit structure of the sealing valve body to effectively lock and open the wrench. This is achieved by using the elastic deformation of the reed. The traditional structure uses the deformation of rubber and non-metallic wrenches to achieve locking and opening operations, but the hot-pressed rubber used in manned spacecraft is hard and the wrench is made of metal. Simply relying on the deformation of hot-pressed rubber requires a lot of force, and astronauts cannot operate in uniform. Using the elastic deformation of the reed can effectively solve the above problems.

[0024] (5) The wrench used in the present invention has a semi-enclosed design, which can effectively prevent possible injuries to astronauts during manual operation while wearing the suit. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0026] Figure 1 This is a structural diagram of a sealing cover device for manual exhaust for emergency use in a manned spacecraft according to an embodiment of the present invention;

[0027] Figure 2 This is an enlarged view of the sealing valve body limiting structure according to an embodiment of the present invention;

[0028] Figure 3 This is a structural diagram of the wrench and the reed after installation according to an embodiment of the present invention;

[0029] Figure 4 This is a structural diagram of a sealing cover according to an embodiment of the present invention. DETAILED DESCRIPTION

[0030] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0031] The present invention proposes a sealing cover device for manual emergency exhaust of a manned spacecraft, which is placed in a piping system in a sealed cabin of the manned spacecraft. It can enable astronauts to manually exhaust the cabin in an emergency situation, while ensuring sealing in non-emergency situations. It has a simple structure, is easy to operate, has reliable sealing, and is highly practical.

[0032] Sealing cover device such as Figure 1As shown, it includes a sealing cover 1, a wrench 2, a sealing valve body 3, a reed 4, a pin 5, and a cap nut 6. A wrench 2 is provided on each side of the sealing cover 1, which are connected by a pin 5 and tightened by a cap nut 6. The sealing cover 1 is connected to the sealing valve body 3 by a pin 5 and tightened by a cap nut 6. The reed 4 is fixed to the wrench 2 by a screw.

[0033] The seal adopts a double-pass seal: there are two circles of sealing rings (roughness 0.8) on the upper end of the sealing valve body 3, and there are two circles of hot-pressed rubber at the position corresponding to the sealing ring on the sealing cover 1. The sealing ring is used to compress the hot-pressed rubber to ensure the seal. In non-emergency situations, the sealing cover 1 is compressed after the two wrenches 2 buckle the sealing valve body 3, and the rubber will be pressed on the sealing ring to ensure the seal in the spacecraft cabin, and the reed 4 provides the sealing force. In an emergency, that is, when the upstream pressure relief valve fails and needs to leave the cabin to relieve pressure, the astronauts can open the wrench 2 first in the suit, and then lift the sealing cover 1 to relieve pressure. At this time, the pin 5 is used as the rotating shaft, and the sealing cover 1 is designed with an extended force arm, so that the astronauts can save more effort when opening the sealing cover to relieve pressure in the suit.

[0034] like Figure 4 As shown, the sealing cover 1 is composed of two limiting bosses 1-1, a sealing cover base 1-2 and a hot-pressed rubber 1-3. The hot-pressed rubber 1-3 is bonded to the sealing cover base 1-2 by a hot vulcanization process, and the bonding strength test is carried out according to the corresponding rubber vulcanization standard to ensure that the bonding is firm and reliable. The hot-pressed rubber 1-3 has two circles, using a double-pass bacteria seal, and the large circle is 0.02mm higher than the small circle. When the sealing cover 1 is closed, the gas in the cabin first passes through the large circle and then through the small circle. The large circle of rubber plays the main sealing role, and the small circle can be regarded as a redundant design of the seal to make the seal more reliable. Two evenly distributed limiting bosses 1-1 are set on the sealing cover 1 to prevent the rubber from being damaged by overpressure or excessive deformation that affects its life.

[0035] The lower end of the sealing valve body 3 can be a pipeline with a separate interface, or it can share a base with other valves to perform integrated module processing to achieve modularization and integration.

[0036] A circular protrusion is designed on the top of the reed 4 so that it will be locked after passing the highest point of the four-way limiting structure of the sealing valve body 3. There are two groups of wrench 2 plus reed 4, which are evenly distributed to ensure that the sealing cover 1 is evenly stressed and the sealing performance is stable.

[0037] like Figure 2 As shown, there is a four-way limit structure on each side of the sealing valve body 3, the highest point of the four-way limit structure is an arc, the two sides are 45° slope and 30° slope respectively, and the top is a R0.5 arc protrusion. Figure 3As shown, the wrench 2 and the reed 4 are connected by screws, with a total of two groups, and there is a circular protrusion on the top of the reed 4. When the wrench 2 is buckled on the sealing valve body 3, the circular protrusion of the reed 4 needs to climb a 30° slope, and will be locked after crossing the highest point of the four-way limit structure. At this time, the climbing angle of 30° is relatively slow and can save effort. When vibrating, it must first pass 45°, and the self-locking cannot be opened. When the wrench 2 needs to be opened, the circular protrusion of the reed 4 climbs a 45° slope, and is released after crossing the highest point of the four-way limit structure. At this time, the climbing angle of 45° is relatively steep, which can prevent the wrench from being vibrated open and affecting the seal in non-emergency situations. The process of locking and opening the wrench 2 is achieved by utilizing the elastic deformation of the reed 4.

[0038] In order to prevent the sharp edge of the reed 4 from causing harm to the astronauts, the wrench 2 is designed to be semi-enclosed. The edge of the reed 4 is wrapped by the wrench 2, so that the astronauts will not touch the edge of the reed when manually putting on the suit, thereby ensuring the safety of the astronauts.

[0039] Except for the hot-pressed rubbers 1-3, all other sealing cover devices are made of metal materials that are compatible with the Class I working fluid in the manned spacecraft.

[0040] The sealing cover device is manually controlled. The sealing cover cooperates with the sealing valve body. When the wrench is tightened, the sealing cover is closed to achieve the sealing function; when the wrench is opened, the sealing cover is manually opened to achieve the emergency exhaust function.

[0041] The above-described embodiments are only preferred specific implementations of the present invention. Common changes and substitutions made by those skilled in the art within the scope of the technical solution of the present invention should be included in the protection scope of the present invention.

Claims

1. A sealing cover device for manual exhaust in emergency of a manned spacecraft, characterized in that: Including sealing cover, wrench, sealing valve body, reed, pin; The sealing cover and the sealing valve body are hinged by pins, the lower surface of the sealing cover is provided with hot-pressed rubber, the upper surface of the sealing valve body is provided with a sealing ring, and the sealing ring cooperates with the hot-pressed rubber; The two wrenches are connected to the two sides of the sealing cover through pins, and the spring is fixed inside the wrenches; In non-emergency situations, the sealing cover is tightened after two wrenches are used to hold the sealing valve body, the hot-pressed rubber is pressed against the sealing ring, and the reed provides sealing force; in emergency situations, the astronauts wear the suit to open the wrench first, and then lift the sealing cover to release the pressure.

2. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 1, characterized in that: The sealing cover includes a sealing cover base and hot-pressed rubber; the hot-pressed rubber is bonded to the sealing cover base by a hot vulcanization process; the hot-pressed rubber has two circles, adopting a double-pass bacterial seal, and the large circle is no higher than the small circle by no more than 0.02mm; when the sealing cover is closed, the gas in the cabin first passes through the large circle, then passes through the small circle, and flows out of the cabin.

3. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 2, characterized in that: The sealing cover is provided with two evenly spaced limiting bosses to prevent the rubber from being damaged by overpressure or excessive deformation that affects its service life.

4. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 2, characterized in that: The sealing valve body has two sealing rings and lugs at both ends of the valve body. In non-emergency situations, the lugs are held with a wrench to press the hot-pressed rubber onto the sealing rings. The lower surface of each lug has a four-way limiting structure, the highest point of which is an arc, with slopes of 45° to 46° and 30° to 31° on both sides, and an R0.5 to 0.6mm arc protrusion on the top.

5. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 4, characterized in that: There is a circular protrusion on the top of the reed. When the wrench is buckled on the support ear, the reed climbs a 30° slope and will be locked when it passes the highest point of the four-way limit structure.

6. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 4, characterized in that: When the wrench is opened, the circular protrusion of the reed climbs the 45° slope and is released after passing the highest point of the four-way limit structure.

7. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 2, characterized in that: Except for the hot-pressed rubber, the rest of the sealing cover device is made of metal materials that are compatible with Level I working fluid in manned spacecraft.

8. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 1, characterized in that: It also includes a cap nut, and a pin connecting the sealing cover and the wrench is tightened with the cap nut.

9. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 1, characterized in that: The sealing cover is designed with an extended lever arm, making it easier for astronauts to open the sealing cover to release pressure while putting on their suit.

10. The sealing cover device for emergency manual exhaust of a manned spacecraft according to claim 1, characterized in that: The wrench is designed to be semi-enclosed, with the edge of the reed wrapped by the wrench, so that astronauts will not touch the edge of the reed when manually operating the suit.

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