Large-size porthole structure of sub-orbital manned spacecraft

Abstract

The invention relates to the technical field of manned airship porthole structures, in particular to a sub-orbital manned airship large-size porthole structure which comprises a window frame installed on the side wall of a porthole, inner side glass and outer side glass are installed in the window frame, and a glass inner gland is installed on the side, away from the outer side glass, of the inner side glass. A glass outer gland is installed on the side, away from the inner side glass, of the outer side glass, and the glass outer gland and the glass inner gland are installed on the window frame. The inner side glass and the outer side glass are installed in the window frame, the requirement of a large-size porthole can be met, meanwhile, the overall weight of the porthole can be effectively reduced by reducing the number of layers of the glass, the carrying efficiency of an airship can be effectively improved by reducing the weight, and the launching cost is reduced; and in the flying process, the maneuverability and the energy consumption efficiency of the spaceship can be improved.

Description

Technical Field

[0001] The invention relates to the technical field of manned spacecraft porthole structures, and in particular to a large-size porthole structure for a suborbital manned spacecraft. Background Art

[0002] The portholes of traditional spacecraft, such as ordinary satellites and some manned spacecraft, are relatively small in size. The main structure used is a multi-layer glass structure, which generally includes an outer protective glass, a middle insulation layer, and an inner pressure-bearing glass. When this structure is used in smaller portholes, it can meet the requirements of structural strength, heat insulation, and radiation protection to a certain extent. However, when it is applied to large-sized portholes of suborbital manned spacecraft, many problems are exposed. As the area of ​​large-sized portholes increases, the weight of the multi-layer glass structure will increase significantly, which is extremely unfavorable for the overall weight control of the spacecraft and will affect the carrying capacity and flight performance of the spacecraft. At the same time, as the size increases, the unevenness of the stress distribution between the glass increases, and it is easy to break or damage when subjected to complex environmental stress in space (such as temperature changes, stress waves generated by micrometeoroid impacts, etc.), reducing the reliability and safety of the portholes.

[0003] Since aircraft generally fly below the stratosphere, the environmental pressure, temperature changes, radiation intensity, etc. they face are very different from the suborbital space environment. Aircraft windows mainly focus on ensuring cabin pressure and passenger vision in a relatively mild environment with a relatively low pressure difference. Their materials and structural strength cannot meet the requirements of large-size windows of suborbital manned spacecraft in the extreme environment of space. For example, the single-layer or double-layer glass structure used in aircraft windows cannot effectively block radiation, insulate heat and keep warm when facing the strong radiation and huge temperature difference in suborbital space. It is also difficult to withstand the high pressure difference in the space environment, and is prone to deformation or even rupture, which cannot guarantee the safety of personnel and equipment inside the spacecraft.

[0004] In summary, the existing technology has obvious defects and deficiencies in the design of large-size portholes for suborbital manned spacecraft, and it is difficult to meet the comprehensive requirements of suborbital manned spacecraft for large-size portholes in terms of structural strength, weight control, heat insulation, radiation protection and reliability. Therefore, there is an urgent need for a new innovative design solution specifically for large-size portholes for suborbital manned spacecraft.

[0005] Therefore, there is an urgent need for a large-sized porthole structure for a suborbital manned spacecraft, which can meet the demand for large-sized portholes while effectively reducing the overall weight of the portholes by reducing the number of glass layers. The reduced weight can improve the spacecraft's carrying efficiency, reduce launch costs, and help improve the spacecraft's maneuverability and energy efficiency during flight. The large-sized portholes provide astronauts and space tourists with a broad field of view, and can provide a more comprehensive and clear visual experience whether it is observing the earth, appreciating space scenes, or monitoring the external environment during space missions, greatly enhancing the functionality and entertainment of suborbital flights. Summary of the invention

[0006] The purpose of the present invention is to provide a large-size porthole structure for a suborbital manned spacecraft to solve the problems existing in the above-mentioned prior art.

[0007] To achieve the above-mentioned purpose, the present invention provides the following solution: a large-size porthole structure of a suborbital manned spacecraft, comprising a window frame installed on the side wall of the porthole, an inner glass and an outer glass installed in the window frame, an inner glass pressure cover is installed on the side of the inner glass away from the outer glass, and an outer glass pressure cover is installed on the side of the outer glass away from the inner glass, and the outer glass pressure cover and the inner glass pressure cover are installed on the window frame.

[0008] Preferably, the inner glass and the outer glass are provided with a limiting frame, and the limiting frame is fixedly connected to the inner wall of the window frame.

[0009] Preferably, sealing gaskets are respectively provided on both sides of the inner glass and the outer glass.

[0010] Preferably, the two sealing gaskets on the side opposite to the inner glass and the outer glass abut against the limiting frame.

[0011] Preferably, the sealing gasket on the side of the inner glass away from the limiting frame abuts against the inner wall of the glass inner pressure cover.

[0012] Preferably, the sealing gasket on the side of the outer glass away from the limiting frame abuts against the inner wall of the glass outer pressure cover.

[0013] Preferably, a plurality of second O-rings are provided between the window frame and the porthole side wall.

[0014] Preferably, a plurality of the second O-rings are mounted on the side wall of the porthole.

[0015] Preferably, a first O-ring is provided between the glass outer pressure cover and the porthole side wall.

[0016] Preferably, the first O-ring is installed on the side wall of the porthole.

[0017] The present invention discloses the following technical effects:

[0018] The present invention can effectively reduce the overall weight of the portholes by reducing the number of glass layers while meeting the demand for large-sized portholes by installing inner glass and outer glass in the window frame. The reduced weight can effectively improve the carrying efficiency of the spacecraft and reduce the launch cost, and also help to improve the maneuverability and energy efficiency of the spacecraft during flight. At the same time, the large-sized portholes provide astronauts and space tourists with a broad field of view, providing a more comprehensive and clear visual experience whether for observing the earth, appreciating space scenes or monitoring the external environment during space missions, thereby effectively improving the functionality and entertainment of suborbital flights. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 It is a schematic diagram of the cross-sectional structure of the present invention;

[0021] Figure 2 This is a schematic diagram of the window frame structure of the present invention;

[0022] Figure 3 This is a schematic diagram of the glass outer pressure cover structure of the present invention;

[0023] Figure 4 This is a schematic diagram of the glass inner pressure cover structure of the present invention;

[0024] Figure 5 This is a schematic diagram of the inner glass structure of the present invention;

[0025] Among them, 1. side wall of porthole; 2. window frame; 3. first O-ring; 4. outer glass pressure cover; 5. sealing gasket; 6. inner glass pressure cover; 7. inner glass; 8. outer glass. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0028] Suborbital flight refers to a flight mission in which a spacecraft enters space and briefly flies at an altitude of about 100 kilometers above the ground, but does not reach the speed required to orbit the earth. Suborbital manned spacecraft are of great significance in the fields of space exploration and space tourism. They allow astronauts or passengers to experience the microgravity environment of space and enjoy the magnificent scenery of the earth.

[0029] Large-sized windows are crucial for suborbital manned spacecraft. On the one hand, they can provide astronauts with a wider field of view, allowing them to better observe the surrounding environment during space observations, monitoring the Earth's surface, and space walks; on the other hand, for space tourists, large-sized windows can greatly enhance the experience of space travel, allowing them to enjoy a clearer and more comprehensive view of the universe and the Earth's landscape.

[0030] Reference Figure 1-Figure 5 The present invention provides a large-size porthole structure of a suborbital manned spacecraft, comprising a window frame 2 installed on a porthole side wall 1, an inner glass 7 and an outer glass 8 installed in the window frame 2, an inner glass pressure cover 6 installed on the side of the inner glass 7 away from the outer glass 8, and an outer glass pressure cover 4 installed on the side of the outer glass 8 away from the inner glass 7, and the outer glass pressure cover 4 and the inner glass pressure cover 6 are installed on the window frame 2.

[0031] The dimensions of the inner glass 7 and the outer glass 8 are both 1.2 meters × 1 meter. The inner glass 7 and the outer glass 8 are made of high-aluminum-silicon glass, which has excellent high-temperature resistance, high strength and good radiation resistance.

[0032] High alumina silicate glass is a glass containing a higher proportion of aluminum oxide. High alumina silicate glass has excellent mechanical strength, heat resistance, chemical corrosion resistance and high transparency.

[0033] Mechanical strength of high alumina silicate glass: The strength of high alumina silicate glass is 8 times that of ordinary soda-lime glass, and it has good impact and compression resistance.

[0034] Heat resistance of high alumina silicate glass: The softening point is as high as over 900℃, and it can withstand extreme high temperatures exceeding 1000℃, making it suitable for high-temperature industries and aerospace fields.

[0035] Chemical corrosion resistance of high alumina silicate glass: It has strong resistance to most acids, alkalis and solvents, and is suitable for chemical, pharmaceutical and other industries.

[0036] Optical properties of high alumina silicate glass: The transmittance in the visible light range can be as high as over 92%, which is suitable for touch screen protection materials and optical instruments.

[0037] The thickness of the inner glass 7 and the outer glass 8 are both 10 mm; the thickness of the outer glass 8 is 10 mm, and the high-aluminum-silica glass components have been specially proportioned and processed so that the outer glass 8 can withstand the high temperature impact and micrometeoroid impact in the extreme environment of space, effectively ensuring the structural integrity of the porthole; the thickness of the inner glass 7 is 10 mm, and the high-aluminum-silica glass has the characteristics of high transparency and low refractive index change, which can ensure that astronauts and passengers get a clear and undistorted view through the porthole, whether observing the earth's terrain or the universe and the stars, they can achieve ideal visual effects.

[0038] The inner glass 7 and the outer glass 8 have the same structure and adopt a quadratic curved surface that is consistent with the overall side wall of the return capsule to optimize the field of view and enhance the structural strength. The curved glass can be perfectly integrated with the streamlined appearance of the spacecraft, reducing aerodynamic resistance while providing better pressure-bearing capacity.

[0039] The window frame 2 is made of a titanium alloy frame, which has high strength, low density and a thermal expansion coefficient similar to that of high-aluminum-silicon glass, effectively reducing stress problems caused by temperature changes.

[0040] Titanium alloy is an alloy made of titanium and other metal elements, with the characteristics of high strength, good corrosion resistance, high heat resistance, etc. The density of titanium alloy is generally around 4.51g / cm3, which is only 60% of steel, but its strength exceeds that of many alloy structural steels. The specific strength (strength / density) of titanium alloy is much greater than that of other metal structural materials, and parts with high unit strength, good rigidity and light weight can be made. In addition, titanium alloy also has good low temperature performance, non-magnetic, low thermal conductivity, low elastic modulus and other characteristics.

[0041] When installing the inner glass 7 and the outer glass 8, first, evenly apply a layer of radiation-resistant high-temperature sealant on the edges of the inner glass 7 and the outer glass 8 and the fitting surface of the window frame 2. The radiation-resistant high-temperature sealant is specially developed for the space environment and can maintain excellent sealing performance for a long time even under high radiation and large temperature fluctuation conditions.

[0042] Radiation-resistant high-temperature sealants are special sealing materials that can maintain their sealing properties in high temperature and radiation environments. Such sealants are often used in nuclear energy, aerospace, electronics and other fields, because the equipment and systems in these fields need to operate in extreme environments.

[0043] Radiation-resistant high-temperature sealants can withstand hot steam, gas, hot and cold water, light fuel oil, lubricants, mineral oil and natural gas up to 900°C. The sealing surface and joints of radiation-resistant high-temperature sealants have excellent adhesion, which can ensure pressure resistance up to 250 bar (255kg / cm2), flanges without sealing rings can withstand pressure up to 450 bar (459kg / cm2), and screw joints can withstand pressure up to 550 bar (561kg / cm2). Radiation-resistant high-temperature sealants have good radiation resistance and are suitable for radiation environments such as nuclear energy. Radiation-resistant high-temperature sealants can resist corrosion from a variety of chemical substances, including light fuel oil, lubricants, crude oil and natural gas. The plasticity of radiation-resistant high-temperature sealants is unlimited, and the sealing film will not break even under the most demanding conditions.

[0044] The window frame 2 is a polygonal ring structure, and a number of connection points are evenly distributed between the window frame 2 and the porthole side wall 1. The window frame 2 is tightly matched with the precise mounting holes pre-set on the porthole side wall 1 of the spacecraft cabin through special high-strength bolts, which can achieve a stable connection between the window frame 2 and the porthole side wall 1 of the spacecraft cabin.

[0045] The contact surfaces between the window frame 2 and the porthole side wall 1 are equipped with high-performance silicone rubber shock-absorbing pads, which have good elastic recovery ability and high and low temperature resistance. They can effectively buffer the severe vibration and impact generated by the spacecraft during the launch phase and space flight, and effectively ensure the stability and safety of the porthole structure during the entire flight mission.

[0046] Silicone rubber shock-absorbing pads are widely used in the field of machinery. They have excellent shock absorption, vibration isolation, wear resistance, corrosion resistance, waterproofness, oil resistance, explosion resistance, high temperature resistance and low temperature resistance. During the operation of mechanical equipment, silicone rubber shock-absorbing pads can play an important role in protecting machines, reducing noise, and relieving vibration. Therefore, they are widely used in automobiles, industrial machinery, construction, electronics, aerospace, medical and other fields.

[0047] Features of silicone rubber shock pads:

[0048] Excellent shock absorption and vibration isolation effects: Silicone rubber material has a high elastic modulus and damping characteristics, which can effectively absorb and disperse vibration energy, reduce the vibration and noise of the machine, and protect the normal operation of mechanical equipment.

[0049] Wear resistance and corrosion resistance: Silicone rubber material has extremely strong chemical stability and heat resistance, can operate stably for a long time in harsh environments, is not easy to age and deform, and has a long service life.

[0050] Waterproof, oil-proof, explosion-proof, high temperature and low temperature resistant properties: These properties enable silicone rubber shock-absorbing pads to operate stably in humid, greasy, high temperature, low temperature and other environments, and are not easily affected by the external environment.

[0051] The outer glass gland 4 and the inner glass gland 6 are made of 6061 aluminum alloy, which is a lightweight material widely used in the aerospace field and is known for its excellent mechanical properties and good processability. The grooves on the outer glass gland 4 and the inner glass gland 6 are used to ensure uniform compression of the sealing gasket 5, which is essential for maintaining the sealing integrity of the porthole. The precise size and shape of the grooves are calculated to ensure consistent sealing pressure under different flight conditions to prevent cabin leakage. The outer glass gland 4 and the inner glass gland 6 are designed to fit the overall curved surface of the spacecraft to reduce structural obtrusions, and are also combined with aerodynamic performance; they help reduce resistance during flight and improve the flight efficiency of the spacecraft. The high strength characteristics of 6061 aluminum alloy help maintain structural integrity, while the grooves ensure effective compression of the sealing gasket.

[0052] 6061 aluminum alloy is a medium-strength aluminum alloy sheet with good corrosion resistance, good weldability, and good oxidation effect. Its main alloying elements are magnesium and silicon, and form Mg2Si phase. If it contains a certain amount of manganese and chromium, it can neutralize the bad effects of iron; sometimes a small amount of copper or zinc is added to improve the strength of the alloy without significantly reducing its corrosion resistance; there is also a small amount of copper in the conductive material to offset the adverse effects of titanium and iron on conductivity; zirconium or titanium can refine the grains and control the recrystallization structure; in order to improve the machinability, lead and bismuth can be added. When Mg2Si is solid-dissolved in aluminum, the alloy has artificial aging hardening function.

[0053] Characteristics of 6061 aluminum alloy:

[0054] Medium Strength: 6061 aluminum alloy has medium strength, good corrosion resistance, weldability and oxidation effect.

[0055] Processing performance: 6061-T651 is the main alloy of 6061 alloy. It is a high-quality aluminum alloy product produced by heat treatment pre-stretching process. Although its strength cannot be compared with 2XXX series or 7XXX series, it has many magnesium and silicon alloy characteristics, and has excellent processing performance, excellent welding characteristics and electroplating properties, good corrosion resistance, high toughness and no deformation after processing, dense material without defects and easy to polish, easy to color film, excellent oxidation effect and other excellent characteristics.

[0056] By installing the inner glass 7 and the outer glass 8 in the window frame 2, the present invention can meet the demand for large-sized portholes and, by reducing the number of glass layers, can effectively reduce the overall weight of the portholes. The reduced weight can effectively improve the carrying efficiency of the spacecraft and reduce the launch cost, and also help to improve the maneuverability and energy efficiency of the spacecraft during flight. At the same time, the large-sized portholes provide astronauts and space tourists with a broad field of view, whether it is observing the earth, appreciating space scenes or monitoring the external environment in space missions, can provide a more comprehensive and clear visual experience, and effectively improve the functionality and entertainment of suborbital flights.

[0057] In a further optimized solution, a limit frame is provided between the inner glass 7 and the outer glass 8, and the limit frame is fixedly connected to the inner wall of the window frame 2. The limit frame can effectively leave a gap between the inner glass 7 and the outer glass 8.

[0058] According to a further optimized solution, sealing gaskets 5 are provided on both sides of the inner glass 7 and the outer glass 8 respectively.

[0059] According to a further optimized solution, two sealing gaskets 5 on the opposite side of the inner glass 7 and the outer glass 8 abut against the limit frame.

[0060] According to a further optimized solution, the sealing gasket 5 on the side of the inner glass 7 away from the limiting frame abuts against the inner wall of the glass inner pressure cover 6 .

[0061] According to a further optimized solution, the sealing gasket 5 on the side of the outer glass 8 away from the limiting frame abuts against the inner wall of the glass outer pressure cover 4 .

[0062] The sealing gasket 5 is a high-performance silicone rubber shock-absorbing pad; a number of sealing gaskets 5 can effectively buffer the severe vibration and impact generated by the spacecraft during the launch phase and space flight, and effectively ensure the stability and safety of the porthole structure during the entire flight mission.

[0063] Silicone rubber can maintain its performance in the temperature range of -100℃ to 300℃, and is particularly suitable for sealing in high temperature and oxidative environments. The size of the sealing gasket 5 is adapted to the window frame 2 and fits tightly to achieve effective sealing. For a rectangular porthole of 1.2 meters by 1 meter, the size of the sealing gasket 5 should be slightly larger than the edge of the porthole to ensure that uniform sealing pressure can be provided over the entire circumference of the porthole.

[0064] According to a further optimized solution, a plurality of second O-rings are provided between the window frame 2 and the porthole side wall 1 .

[0065] According to a further optimized solution, a plurality of second O-rings are installed on the porthole side wall 1 .

[0066] According to a further optimized solution, a first O-ring 3 is provided between the glass outer pressure cover 4 and the porthole side wall 1 .

[0067] According to a further optimized solution, the first O-ring 3 is installed on the porthole side wall 1 .

[0068] The first O-ring 3 and the second O-ring are made of silicone rubber to ensure reliability in extreme temperature and chemical environments. At the same time, considering the particularity of the porthole, a special installation process is required. The first O-ring 3 and the second O-ring are made of fluoroplastic rubber O-ring molding process to reduce the friction coefficient, increase the medium resistance of the seal, and meet the long life requirements.

[0069] Referring to Table 1, the porthole is a key part connecting the inside and outside of the spacecraft. The larger the size, the greater the structural requirements for installing the porthole. A larger porthole means that stronger support and stability are required to withstand the internal pressure difference. The structural materials of the porthole are shown in Table 1. Among them, the porthole side wall 1 is made of weldable 5A06 grade aluminum alloy, and the inner glass 7 and the outer glass 8 are made of high aluminum silicon glass.

[0070] Table 1

[0071]

[0072] 5A06 aluminum alloy is an Al-Mg series rust-proof aluminum with high strength and corrosion stability, and good plasticity in annealing and extrusion state. Its main alloying element is magnesium, which has good corrosion resistance and weldability, as well as medium strength. The excellent corrosion resistance makes 5A06 alloy widely used in maritime applications such as ships, as well as automobiles, aircraft welding parts, subway light rails, pressure vessels that require strict fire protection (such as liquid tankers, refrigerated trucks, refrigerated containers), refrigeration equipment, TV towers, drilling equipment, transportation equipment, missile parts, armor, etc.

[0073] 5A06 aluminum alloy has good mechanical properties, with a tensile strength of 315MPa, a yield strength of 210MPa, and an elongation of 10%. This medium-strength aluminum alloy material can still maintain good performance under high temperature and wide temperature change conditions, so it has important application value in the aerospace and military fields.

[0074] In the description of the present invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0075] The embodiments described above are only descriptions of the preferred modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A large-size porthole structure for a suborbital manned spacecraft, characterized in that: The invention comprises a window frame (2) mounted on a porthole side wall (1), wherein an inner glass (7) and an outer glass (8) are mounted in the window frame (2), an inner glass pressure cover (6) is mounted on a side of the inner glass (7) away from the outer glass (8), and an outer glass pressure cover (4) is mounted on a side of the outer glass (8) away from the inner glass (7), and the outer glass pressure cover (4) and the inner glass pressure cover (6) are mounted on the window frame (2).

2. The large-size porthole structure of a suborbital manned spacecraft according to claim 1, characterized in that: The inner glass (7) and the outer glass (8) are provided with a limit frame, and the limit frame is fixedly connected to the inner wall of the window frame (2).

3. The large-size porthole structure of a suborbital manned spacecraft according to claim 2, characterized in that: Sealing gaskets (5) are respectively provided on both sides of the inner glass (7) and the outer glass (8).

4. The large-size porthole structure of a suborbital manned spacecraft according to claim 3, characterized in that: The two sealing gaskets (5) on the opposite side of the inner glass (7) and the outer glass (8) are in contact with the limiting frame.

5. The large-size porthole structure of a suborbital manned spacecraft according to claim 3, characterized in that: The sealing gasket (5) on the side of the inner glass (7) away from the limiting frame abuts against the inner wall of the glass inner pressure cover (6).

6. The large-size porthole structure of a suborbital manned spacecraft according to claim 3, characterized in that: The sealing gasket (5) on the side of the outer glass (8) away from the limiting frame abuts against the inner wall of the glass outer pressure cover (4).

7. The large-size porthole structure of a suborbital manned spacecraft according to claim 1, characterized in that: A plurality of second O-rings are arranged between the window frame (2) and the porthole side wall (1).

8. The large-size porthole structure of a suborbital manned spacecraft according to claim 7, characterized in that: A plurality of the second O-rings are mounted on the porthole side wall (1).

9. The large-size porthole structure of a suborbital manned spacecraft according to claim 1, characterized in that: A first O-ring (3) is provided between the glass outer pressure cover (4) and the porthole side wall (1).

10. The large-size porthole structure of a suborbital manned spacecraft according to claim 9, characterized in that: The first O-ring (3) is mounted on the porthole side wall (1).

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