A kind of for carrying fairing outer rain-proof and heat-proof function's mouth cover

Abstract

The application discloses a port cover with rainproof and heatproof functions outside a fairing, and belongs to the field of overall design of spacecrafts. The port cover comprises a ground test port cover before launching of the spacecraft and an ascending section port cover, and rainproof of the ground test port cover and rainproof and heatproof of the ascending section port cover are simultaneously considered. The port cover has the advantages of rainproof and heatproof functions, quick dismounting and mounting, manual and quick installation before personnel evacuation under the condition that the time is limited before launching of the tower, and has wide application prospects in the field of space vehicles.

Description

Technical Field

[0001] This invention relates to the field of spacecraft overall design, and in particular to a cover for a launch fairing that has rainproof and heatproof functions. Background Technology

[0002] During flight test missions, spacecraft operate in high-temperature and high-humidity environments. To maintain positive pressure within the spacecraft cabin and prevent condensation, the spacecraft-rocket assembly requires continuous air conditioning after the launch pad is in place until 30 minutes before launch. The design of the air conditioning vents must prevent rainwater from entering the spacecraft cabin and affecting equipment functionality, while also considering heat protection for the area during the spacecraft's ascent. If an open launch pad is used, operators can only work via a connecting corridor before launch. In this case, the installation of the air conditioning vent covers must be quick and easy, allowing operators to safely evacuate the launch pad within a limited time. Summary of the Invention

[0003] The technical problem solved by this application is to overcome the shortcomings of existing technologies and provide a rainproof and heat-resistant cover for the outside of a launch vehicle fairing. This cover can be used on the outside of a launch vehicle fairing and can be manually and quickly docked. The solution includes a ground testing cover and an ascent stage cover used together, enabling air supply from the launch tower while providing rainproof and heat-resistant protection and high operability. It improves the operational efficiency of launch tower operations while ensuring rainproof and heat-resistant functions.

[0004] The technical solution provided in this application is as follows:

[0005] A rainproof and heatproof cover for the fairing of a launch vehicle is connected to a cover mounting interface, which is located on the part of the spacecraft exposed outside the fairing. The cover includes a ground test cover and an ascent stage cover.

[0006] The cover mounting interface includes an air supply port, two mounting through holes, and two mounting screw holes. The air supply port, mounting through holes, and mounting screw holes are all opened on the spacecraft's cabin wall. The two mounting through holes are located on both sides of the air supply port, and the two mounting screw holes are located on both sides of the air supply port. The line connecting the two mounting through holes intersects the line connecting the two mounting screw holes.

[0007] The ground test port cover includes a ground test port cover body and two captive screws. The two captive screws pass through the ground test port cover body and are installed on the spacecraft's cabin wall through mounting screw holes. The ground test port cover body is provided with a connection pipe port for connecting to the air conditioning supply pipe.

[0008] The ascending section cover includes an air supply cover body and two spring locking mechanisms, which are installed on the spacecraft bulkhead through mounting through holes.

[0009] During pre-launch ground testing, the ground test hatch is installed on the hatch installation interface. Air conditioning is supplied through the ground test hatch until a fixed time before launch. The ground test hatch is then removed from the hatch installation interface, and the ascent stage hatch is installed on the hatch installation interface.

[0010] The cover installation interface also includes a square groove, which is formed on the outer wall of the spacecraft cabin. The ground test cover body and the air supply cover body both mate with the square groove. When the ground test cover body or the air supply cover body is located in the square groove, its surface is flush with the outer wall of the spacecraft cabin.

[0011] The rising section cover also includes a rising rainproof sealing ring, which is installed on the inner side of the air outlet cover body, and the diameter of the air outlet hole is not greater than the inner diameter of the rising rainproof sealing ring.

[0012] The rising section cover also includes a heat-insulating layer material, which is installed on the outside of the air outlet cover body.

[0013] The spring locking mechanism includes a locking key and a spring. Two protrusions are provided on the inner side of the air outlet cover body. An installation groove is provided on the side of the protrusions that are opposite to each other. The locking key slides in the installation groove along the diagonal direction of the protrusion. One end of the spring contacts the bottom of the installation groove and the other end is installed on the locking key. The locking key extends out of the other end of the installation through hole.

[0014] The spring lock mechanism also includes a screw, and the protrusion is provided with a waist-shaped hole. The fixing hole is connected to the mounting groove. The end of the screw is threaded to the lock key. The screw is located in the waist-shaped hole and can move along the length of the waist-shaped hole.

[0015] The mounting hole penetrates the spacecraft's bulkhead so that the screw is located inside the spacecraft bulkhead.

[0016] The spacecraft cabin wall has an equipment operation port on the side of the hatch installation interface, through which a hand can be reached into the cabin to adjust the spring lock mechanism.

[0017] The ground test port cover also includes a ground rainproof sealing ring, which is glued to the inside of the ground test port cover. The diameter of the air supply hole is not greater than the inner diameter of the ground rainproof sealing ring.

[0018] Polyimide tape is adhered to the surface of the head of the non-detachable screw, and the polyimide tape also covers the surface of the ground test port cover body located around the head of the non-detachable screw.

[0019] In summary, this application includes at least the following beneficial technical effects:

[0020] 1) The design of this invention takes into account both ground testing and flight ascent conditions. The two cover designs are used in combination to solve the problem of air supply and temperature regulation of the ground air conditioning system for the rocket assembly before launch, while also taking into account the installation of the cover during flight ascent.

[0021] 2) The two schemes of this invention have carried out rainproof design under the ground test conditions of spacecraft and rainproof and heat protection design during the flight ascent period. They can be applied to harsh environments such as outside the fairing of launch vehicles to ensure the stability of the spacecraft cabin environment, provide stable and reliable support for cabin equipment, and ensure the safety and functionality of the equipment. They have broad application prospects in the field of overall spacecraft design.

[0022] 3) In this invention, the ascending section cover utilizes a spring-lock mechanism for quick disassembly. During tower-connecting corridor operations, only one operator is needed to quickly complete the installation, as the quick-release lock body of the cover is self-locking, eliminating the need for additional safety measures. Within the limited 30 minutes of operation time before launch, this invention's ascending section cover design allows for rapid manual docking and installation, effectively improving tower operation efficiency.

[0023] 4) The installation of the ascending section cover of this invention does not require the use of operating tools and does not involve the introduction of screws or other fasteners, thus avoiding the risk of tools slipping and foreign objects being introduced during high-altitude operations. The operation is simple and reliable, ensuring the reliability and safety of tower operations for operators. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the launch state layout of the rising section cover according to a preferred embodiment of the present invention;

[0025] Figure 2 This is a schematic diagram of the installation of the ascending section cover according to a preferred embodiment of the present invention (from inside the cabin to outside the cabin);

[0026] Figure 3 This is a schematic diagram of the rising section cover assembly according to a preferred embodiment of the present invention;

[0027] Figure 4 Figure 1 is a schematic diagram of the spring locking mechanism in the ascending section cover of the present invention, wherein Figure 2a is a structural diagram of the spring locking mechanism, Figure 3b is a cross-sectional view of the installation interface of the cover on the spacecraft cabin wall and the air supply cover body, and Figure 4c is a schematic diagram of the cover installation interface from the outside of the cabin to the inside of the cabin.

[0028] Figure 5 This is a schematic diagram of the ground test port cover composition according to a preferred embodiment of the present invention;

[0029] Figure 6 This is a schematic diagram of the installation of the ground test port cover according to a preferred embodiment of the present invention.

[0030] Explanation of reference numerals in the attached drawings: 1. Spacecraft; 2. Fairing;

[0031] 3. Cover mounting interface; 31. Square groove; 32. Mounting through hole; 34. Mounting screw hole; 35. Air supply hole;

[0032] 41. Ground test port cover body; 42. Ground rainproof sealing ring; 43. Non-removable screw;

[0033] 51. Air outlet cover body; 511. Protrusion; 52. Heat insulation layer material; 53. Rising rainproof sealing ring; 54. Spring lock mechanism;

[0034] 541. Locking key; 542. Spring; 543. Screw. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the present invention clearer, the following will describe in detail, with reference to the accompanying drawings, a design for a rainproof and heat-resistant cover for a carrier fairing provided by the present invention. This embodiment is implemented under the premise of the technical solution of the present invention, and provides detailed implementation methods and specific operating procedures. However, the scope of protection of the present invention is not limited to the following embodiment. Those skilled in the art can modify and refine it without changing the spirit and content of the present invention.

[0036] A rainproof and heat-resistant cover for use on the outside of a carrier fairing, such as Figure 1 , Figure 2 and Figure 6 As shown, the spacecraft includes a ground test hatch and an ascent stage hatch for pre-launch testing of Spacecraft 1. To improve the load-bearing capacity of the launch vehicle carrying Spacecraft 1, a smaller fairing 2 was designed. Most of the structure of Spacecraft 1 is exposed outside the fairing 2; that is, Spacecraft 1 consists of an upper part and a lower part, with the upper part of Spacecraft 1 exposed outside the fairing 2. The hatch mounting interface 3 is located on the upper part of Spacecraft 1. The hatch mounting interface 3 is used to install the ground test hatch or the ascent stage hatch.

[0037] The ground test hatch and the ascent hatch can be used together in two situations: pre-launch ground testing and ascent phase flight. Specifically, during pre-launch ground testing, the ground test hatch is installed, and air conditioning is supplied through the ground test hatch until 30 minutes before launch. Then, the ground test hatch is removed from hatch installation interface 3, and the ascent hatch is quickly replaced to allow operators to safely evacuate the launch tower within a limited time.

[0038] like Figure 4As shown in Figure c, the cover mounting interface 3 is located on the bulkhead of spacecraft 1. The cover mounting interface 3 includes a square groove 31, mounting through holes 32, mounting screw holes 34, and air supply holes 35. The square groove 31 is located on the outer wall of the bulkhead of spacecraft 1. The air supply hole 35 is located in the middle of the square groove 31 and penetrates the bulkhead of spacecraft 1, allowing air conditioning to enter the bulkhead of spacecraft 1. Two mounting through holes 32 are provided in the square groove 31 along one diagonal line of the square groove 31. The mounting through holes 32 penetrate the bulkhead of spacecraft 1 and are located near the edges of the square groove 31. The mounting through holes 32 are used to install the ascent section cover. Two mounting screw holes 34 are provided in the square groove 31 along the other diagonal line of the square groove 31. The two mounting screw holes 34 are used to install the ground test cover. The mounting screw holes 34 do not penetrate the bulkhead of spacecraft 1.

[0039] like Figure 5 and Figure 6 As shown, the ground test port cover includes a ground test port cover body 41, a ground rainproof sealing ring 42, and captive screws 43. The ground test port cover body 41 mates with a square groove 31. After the ground test port cover body 41 is inserted into the square groove 31, the surface of the ground test port cover body 41 is flush with the outer wall of the spacecraft 1 cabin. The ground rainproof sealing ring 42 is glued to the inner side of the ground test port cover mounting surface. Its cross-section is Ω-shaped. The diameter of the air supply hole 35 is not larger than the inner diameter of the ground rainproof sealing ring 42. The ground test port cover is sealed to the spacecraft 1 cabin by the compression deformation of the ground rainproof sealing ring 42 and the bottom of the square groove 31. One ground test port cover body 41 is connected to two captive screws 43. The two captive screws 43 are diagonally arranged and threaded into the mounting screw holes 34. The ground test port cover body 41 is provided with a connection port for connecting to the air conditioning air supply pipe. It is fixed to the spacecraft 1 cabin by the two diagonally installed captive screws 43. After installation, attach polyimide tape to the head of the non-detachable screw 43 to prevent rainwater from entering the cabin through the mounting screw hole 34.

[0040] During the air supply operation of the tower ground air conditioning system, the ground test port cover is secured to the bulkhead of spacecraft 1 using two self-locking screws 43 located diagonally on the ground. Before installation, a ground rainproof sealing ring 42 is affixed to the inside of the ground test port cover. After installation, polyimide tape is affixed to the head of the self-locking screws 43 to ensure good rainproof performance of the port cover during ground testing.

[0041] like Figure 3 and Figure 4As shown, the rising section cover includes an air outlet cover body 51, a heat-insulating layer material 52, a rising rainproof sealing ring 53, and a spring locking mechanism 54. The heat-insulating layer material 52 is glued to the outside of the air outlet cover body 51, and the rising rainproof sealing ring 53 is glued to the inside of the air outlet cover body 51. The heat-insulating layer material 52 and the rising rainproof sealing ring 53 provide rainproof and heat-insulating functions for the cover, ensuring the reliability and safety of equipment installation in the rising section cover area. Two protrusions 511 are provided diagonally on the inside of the air outlet cover body 51. The spring locking mechanism 54 is connected to the protrusions 511 and cooperates with the mounting through hole 32 to achieve installation.

[0042] The ascent section cover has two mounting interfaces with the spacecraft 1 cabin structure, with the spring locking mechanisms 54 installed diagonally in pairs. The inner side of the air supply cover body 51 is rainproofed by an adhesive sealing ring, and the outer surface of the air supply cover body 51 is covered with a heat-insulating layer material 52 to meet the heat protection requirements of spacecraft 1 during flight ascent.

[0043] like Figure 4 As shown in Figures a and b, the spring locking mechanism 54 includes a locking key 541, a spring 542, and a screw 543. The protrusion 511 has a mounting groove on the side opposite to the ventilation hole. The locking key 541 slides in the mounting groove along the diagonal direction of the protrusion 511. One end of the spring 542 contacts the bottom of the mounting groove, and the other end is installed on the locking key 541. The protrusion 511 also has an oblong hole. The fixing hole communicates with the mounting groove. The end of the screw 543 is threaded to the locking key 541. The screw 543 is located in the oblong hole and can move along the length of the oblong hole. The fixing hole limits the screw 543. When the screw 543 is installed in the fixing hole, the axis of the screw 543 is perpendicular to the air outlet cover body 51. During the installation of the ascending section cover, as the air outlet cover body 51 gradually enters the square groove 31, the spring locking mechanism 54 also simultaneously enters the mounting through hole 32. At the same time, the locking key is pressed against the end of the mounting through hole 32 and moves towards the air outlet 35 until it extends beyond the other end of the mounting through hole 32. Then, driven by the spring, the locking key moves away from the air outlet 35, achieving self-locking. At this point, the locking key 541 and the air outlet cover body 51 are located on opposite sides of the spacecraft 1 cabin wall. Because the locking key 541 is driven by the spring, it is not directly aligned with the mounting through hole 32, thus fixing the ascending section cover to the spacecraft 1 cabin structure. When removing the ascending section cover, the operator moves the screw 543 in the opposite direction of the limit through the equipment operating port on the right side of the ascending section cover to remove it from the spacecraft 1 cabin wall.

[0044] The ascent section hatch is installed quickly using two diagonally arranged spring-locking mechanisms 54. After installation, no safety locking is required; the spring-locking mechanisms 54 themselves are self-locking. The installation of the ascent section hatch is simple, allowing for rapid and reliable docking with the hull structure even with limited time (30 minutes before launch), effectively improving tower operation efficiency. To remove the ascent section hatch, the operator reaches into the hull through the equipment access port on the right side of the hatch and simultaneously moves the screws 543 on the two diagonally arranged spring-locking mechanisms 54 in the opposite direction along the spring axis. Once unlocked, the hatch is removed from the hull.

[0045] The ground test hatch and the ascent stage hatch are used together to meet the air supply needs of the spacecraft's first compartment before launch. They can be installed quickly, are easy to operate, and are stable and reliable, giving operators more time to evacuate the launch tower before launch.

[0046] The contents not described in detail in this application specification are common knowledge to those skilled in the art.

[0047] The present application has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present application. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and implementation methods of the present application without departing from the spirit and scope of the present application, and all such modifications and improvements fall within the scope of the present application. The scope of protection of the present application is determined by the appended claims.

Claims

1. A rainproof and heat-resistant cover for use on the outside of a transport fairing, characterized in that: Connected to the hatch mounting interface (3), the hatch mounting interface (3) is located on the part of the spacecraft (1) exposed outside the fairing (2), the hatch includes a ground test hatch and an ascent hatch; The cover mounting interface (3) includes an air supply hole (35), two mounting through holes (32) and two mounting screw holes (34). The air supply hole (35), the mounting through holes (32) and the mounting screw holes (34) are all opened on the bulkhead of the spacecraft (1). The two mounting through holes (32) are located on both sides of the air supply hole (35), and the two mounting screw holes (34) are located on both sides of the air supply hole (35). The line connecting the two mounting through holes (32) intersects the line connecting the two mounting screw holes (34). The ground test cover includes a ground test cover body (41) and two captive screws (43). The two captive screws (43) pass through the ground test cover body (41) and are installed on the cabin wall of the spacecraft (1) through the mounting screw holes (34). The ground test cover body (41) is provided with a connecting pipe port for connecting to the air conditioning supply pipe. The ascending section cover includes an air supply cover body (51) and two spring locking mechanisms (54), which are installed on the bulkhead of the spacecraft (1) through mounting through holes (32); During the ground test before launch, the ground test cover is installed on the cover installation interface (3). Air conditioning is supplied through the ground test cover until a fixed time before launch. The ground test cover is then removed from the cover installation interface (3), and the ascending section cover is installed on the cover installation interface (3).

2. A rainproof and heat-resistant cover for a transport fairing according to claim 1, characterized in that: The cover mounting interface (3) also includes a square groove (31). The square groove (31) is opened on the outer wall of the spacecraft (1) cabin. The ground test cover body (41) and the air supply cover body (51) both cooperate with the square groove (31). When the ground test cover body (41) or the air supply cover body (51) is located in the square groove (31), its surface is flush with the outer wall of the spacecraft (1) cabin.

3. A rainproof and heat-resistant cover for a transport fairing according to claim 1, characterized in that: The rising section cover also includes a rising rainproof sealing ring (53), which is installed on the inner side of the air outlet cover body (51). The diameter of the air outlet hole (35) is not greater than the inner diameter of the rising rainproof sealing ring (53).

4. A rainproof and heat-resistant cover for a transport fairing according to claim 1, characterized in that: The rising section cover also includes a heat-insulating layer material (52), which is installed on the outside of the air outlet cover body (51).

5. A rainproof and heat-resistant cover for a transport fairing according to claim 1, characterized in that: The spring locking mechanism (54) includes a locking key (541) and a spring (542). Two protrusions (511) are provided on the inner side of the air outlet cover body (51). An installation groove is provided on the side of the protrusions (511) that are opposite to each other. The locking key (541) slides in the installation groove along the diagonal direction of the protrusions (511). One end of the spring (542) contacts the bottom of the installation groove and the other end is installed on the locking key (541). The locking key (541) extends out of the other end of the installation through hole (32).

6. A rainproof and heat-resistant cover for a transport fairing according to claim 5, characterized in that: The spring lock mechanism (54) also includes a screw (543), and the protrusion (511) is also provided with a waist-shaped hole. The waist-shaped hole is connected to the mounting groove. The end of the screw (543) is threaded to the lock key (541). The screw (543) is located in the waist-shaped hole and can move along the length of the waist-shaped hole.

7. A rainproof and heat-resistant cover for a transport fairing according to claim 6, characterized in that: The mounting through hole (32) penetrates the bulkhead of the spacecraft (1) so that the screw (543) is located inside the bulkhead of the spacecraft (1).

8. A rainproof and heat-resistant cover for a transport fairing according to claim 1, characterized in that: The spacecraft (1) has an equipment operation port on the side of the hatch installation interface (3) on the cabin wall. The user can reach into the cabin through the equipment operation port to adjust the spring lock mechanism (54).

9. A rainproof and heat-resistant cover for a transport fairing according to claim 1, characterized in that: The ground test port cover also includes a ground rainproof sealing ring (42), which is glued to the inside of the ground test port cover. The diameter of the air supply hole (35) is not greater than the inner diameter of the ground rainproof sealing ring (42).

10. A rainproof and heat-resistant cover for a carrier fairing according to claim 1, characterized in that: Polyimide tape is pasted on the head surface of the non-detachable screw (43), and the polyimide tape also covers the surface of the ground test port cover body (41) located around the head of the non-detachable screw (43).

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