A fall arrest device for launch vehicle extravehicular test operations

Abstract

The utility model provides a kind of for carrying rocket out-of-cabin test operation's anti-falling device, belong to carrying rocket field, solve how to realize the problem of out-of-cabin anti-falling measure unmanned;Including fixed connecting piece, object bag and slide rail;Fixed connecting piece's inside has cavity structure;By increasing the volume of cavity structure, increase and atmospheric pressure intensity difference adsorption installation in the lower of carrying rocket out-of-cabin falling target;Slide rail includes pulley and track, pulley includes spherical portion and extension, spherical portion and extension integrated molding;The shape of the slide of track and spherical portion is adapted;Pulley is fixed in object bag opening portion;Track is installed on the shell outer wall of fixed connecting piece around;Pulley enters track, extension extends the outside of slide, after spherical portion is adjusted to the direction and angle of object bag along slide, and the falling target of carrying rocket out-of-cabin is caught;The utility model realizes the unmanned of out-of-cabin anti-falling measure, reduces operation risk.

Description

Technical Field

[0001] This utility model belongs to the field of launch vehicle technology, and in particular relates to a fall protection device for external test operations of launch vehicles. Background Technology

[0002] The testing of launch vehicles at space launch sites and assembly plants involves numerous extravehicular activities. During these extravehicular testing operations, debris may fall onto the launch vehicle's extravehicular operation platform, posing a significant safety hazard to the platform and the personnel conducting the extravehicular testing on the launch vehicle.

[0003] Currently, the fall protection measures for the external test operating system of launch vehicles all require manual assistance. Although this has solved the safety hazards to a certain extent, it has also made it impossible for a single person to complete the external test operation of launch vehicles independently, which affects work efficiency.

[0004] Therefore, fall arrestors that do not require manual assistance play a crucial role in extravehicular activity (EVA) testing of launch vehicles. They ensure the safety of the external environment, reduce operational risks, and improve the work efficiency of EVA personnel. Thus, there is an urgent need for a fall arrestor for EVA testing of launch vehicles. Utility Model Content

[0005] To address the challenges of reducing the risks associated with extravehicular activity (EVA) testing of launch vehicles and improving the work efficiency of EVA personnel, this invention proposes a fall protection device for EVA testing. This device utilizes a unique drying structure with a certain curvature and painted exterior wall of the launch vehicle to achieve unmanned EVA fall protection, effectively reducing operational risks for EVA personnel and improving their work efficiency.

[0006] To achieve the above objectives, this utility model is specifically implemented through the following technical solution:

[0007] This utility model provides a fall protection device for external test operations of a launch vehicle, including a fixed connector 10, a cargo bag 20 and a slide rail 30;

[0008] The fixed connector 10 has a cavity structure inside; the fixed connector 10 is installed below the target falling outside the launch vehicle cabin by increasing the volume of the cavity structure and increasing the pressure difference with atmospheric pressure.

[0009] The carrying bag 20 includes a shape expansion member 21 and a load-bearing member 22; the shape expansion member 21 is connected to the top of the load-bearing member 22, and the shape expansion forms an adjustable opening of the carrying bag 20; the bottom of the load-bearing member 22 is sealed, forming the carrying part of the carrying bag 20.

[0010] The slide rail 30 includes a pulley 31 and a track 32. The pulley 31 includes a spherical portion and an extension portion, which are integrally formed. The track 32 has a slide 322, which is adapted to the shape of the spherical portion.

[0011] The pulley 31 is fixed to the opening of the cargo bag 20; the track 32 is installed around the outer wall of the housing 11 of the fixed connector 10; the pulley 31 enters the track 32, the extension extends out of the outside of the slide 322, and the spherical part slides along the slide 322 to adjust the direction and angle of the cargo bag 20, and then catches the falling target outside the launch vehicle cabin.

[0012] Furthermore, the number of fixed connectors 10 corresponds to the number of slide rails 30, and includes at least two.

[0013] The fixed connector 10 includes a housing 11, a threaded seat 12, a threaded rod 13, a rotating handle 14, a sealing plate 15, and a sealing gasket 16; wherein the thread dimensions of the threaded seat 12 and the threaded rod 13 meet the tolerance matching requirements.

[0014] The housing 11 is a cavity structure with an open bottom, and the outer wall of the housing 11 has a mounting groove for the track 32;

[0015] The threaded seat 12 passes through and is fixed at the top center of the housing 11;

[0016] The rotating handle 14 and the sealing plate 15 are respectively installed at both ends of the threaded rod 13;

[0017] After the threaded rod 13 passes through the threaded through hole of the threaded seat 12 through the external thread, the rotating handle 14 is placed on the outside of the housing 11, and the sealing plate 15 is built into the cavity structure of the housing 11, so the edge of the sealing plate 15 is in close contact with the inner wall of the cavity structure.

[0018] The sealing gasket 16 is installed at the bottom edge of the housing 11 but is not completely sealed, preventing the sealing plate 15 from extending out of the bottom of the housing 11;

[0019] When the fixed connector 10 is in use, the sealing plate 15 is tightly attached to the bottom inner wall of the sealing gasket 16; below the target outside the launch vehicle cabin, after the bottom outer wall of the sealing gasket 16 is tightly attached to the outer wall of the launch vehicle cabin, the rotating handle 14 is turned to drive the threaded rod 13 to rotate in the threaded seat 12, raising the sealing plate 15 and separating it from the bottom inner wall of the sealing gasket 16. The volume of the cavity structure increases, the pressure difference with atmospheric pressure increases, and the sealing gasket 16 is adsorbed and installed on the outer wall of the launch vehicle cabin.

[0020] When the fixed connector 10 is replaced, the rotating handle 14 is rotated in the opposite direction, which drives the threaded rod 13 to rotate in the opposite direction in the threaded seat 12. The sealing plate 15 descends, the volume of the cavity structure decreases, the pressure difference with atmospheric pressure decreases, and the sealing gasket 16 is removed from the outer wall of the launch vehicle cabin.

[0021] The sealing gasket 16 is designed with deformable material and is covered with anti-slip rubber.

[0022] The design formula for the fixed connector 10 is as follows:

[0023]

[0024] Wherein, G1 is the weight borne by a single fixed connector 10, G0 is the weight of a single fixed connector 10 itself, μ is the coefficient of friction between the fall arrestor and the outer wall of the launch vehicle cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing gasket 16, S0 is the area of ​​the bottom of the shell 11 that is not completely sealed, h1 is the height of the threaded rod 13 rotating upward, the maximum value of h1 is the depth of the cavity structure, S1 is the contact area between the fall arrestor and the launch vehicle, and θ is the angle between the installation position of the fall arrestor and the horizontal plane, θ is 0 to 90°.

[0025] Furthermore, the fixed connector 10 has a built-in pressure regulating device that increases the volume of the cavity structure; the pressure regulating device includes a gravity sensor 41, a processing component 43, and a motor 44;

[0026] The gravity sensor 41 is built into the sealing gasket 16, the processing component 43 is built into the threaded seat 12, and the motor 44 is embedded in the threaded seat 12 and fixedly connected to the internal thread 17; the gravity sensor 41 is connected to the processing component 43 through the cable 42, and the processing component 43 is connected to the motor 44 through the cable 42.

[0027] The gravity sensor 41 converts the received gravity signal from the fall arrestor into an electrical signal and feeds it back to the processing component 43 via cable 42. The processing component 43 outputs the obtained target pressure as an electrical signal and sends it to the motor 44 via cable 42. The motor 44 drives the internal thread 17 in the threaded seat 12 to rotate, causing the threaded rod 13 to rotate upward according to the principle of relative motion. The volume of the cavity structure increases, the pressure difference between the inside and outside increases, and the adsorption force between the fixed connector 10 and the outer wall of the launch vehicle cabin increases. When the depth of the cavity structure reaches the critical value, the processing component 43 issues an alarm signal to prompt the replacement of the fall arrestor.

[0028] The formula for calculating the target pressure obtained by the processing component 43 is as follows:

[0029]

[0030] Wherein, G1 is the weight borne by a single fixed connector 10, G0 is the weight of a single fixed connector 10 itself, μ is the coefficient of friction between the fall arrestor and the outer wall of the launch vehicle cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing gasket 16, S0 is the area of ​​the bottom of the shell 11 that is not completely sealed, h1 is the height of the threaded rod 13 rotating upward, the maximum value of h1 is the depth of the cavity structure, S1 is the contact area between the fall arrestor and the launch vehicle, and θ is the angle between the installation position of the fall arrestor and the horizontal plane, θ is 0 to 90°.

[0031] Furthermore, the slide rail 30 has a locking device;

[0032] The locking device includes a locking part disposed on the pulley 31 and at least one limiting groove 321 disposed in the slide rail 322;

[0033] The locking part is placed into the corresponding limiting groove to lock the relative position of the pulley 31 on the track 32; after the locking part is moved out of the limiting groove, the pulley 31 slides in the track 32.

[0034] Furthermore, the locking part includes a locking unit disposed on the spherical part and an unlocking unit disposed on the extension part;

[0035] The unlocking unit includes an unlocking button 311, an unlocking spring 312, and an unlocking slider 313; the lower end of the unlocking button 311 is built into the extension, and the bottom end is connected to the top end of the unlocking spring 312, and the bottom end of the unlocking spring 312 is connected to the top end of the unlocking slider 313.

[0036] The locking unit includes a locking slide 315, a locking spring 316, and a locking key 317, wherein the locking key 317 is adapted to the shape of the limiting groove 321; the lower end of the locking key 317 is built into the spherical part, the bottom end is connected to the top end of the locking slide 315, and the bottom end of the locking slide 315 is connected to the locking spring 316.

[0037] The locking slide 315 and the unlocking slide 313 are connected by a hinge on the connecting rod 314;

[0038] The elastic coefficient of the locking spring 316 is greater than that of the unlocking spring 312. When no external force is applied to the unlocking button 311, the unlocking spring 312 is in a naturally extended state and the locking spring 316 is in a naturally compressed state. At this time, the locking key 317 pops up and gets into the limiting groove 321 to achieve the locking state.

[0039] When a pulling force is applied to the unlock button 311, the unlock spring 312 is in a stretched state, the unlock slider 313 moves upward, causing the connecting rod 314 to rotate, the locking slider 315 moves downward, causing the locking key 317 to move downward, the locking spring 316 is compressed, and the locking key 317 disengages from the limiting groove 321, thus achieving the unlocked state.

[0040] Furthermore, one or more of the cargo bags 20 are used for nesting;

[0041] There is a gap between the stacked bags 20, and the volume of the lower stacked bag 20 is larger than the volume of the current stacked bag 20.

[0042] The working principle and process of this utility model include:

[0043] As needed, wipe the installation location of the fall arrestor below the target outside the launch vehicle compartment;

[0044] The sealing plate 15 of the fixed connector 10 is tightly attached to the bottom inner wall of the sealing gasket 16; below the target outside the launch vehicle cabin, after the bottom outer wall of the sealing gasket 16 is tightly attached to the outer wall of the launch vehicle cabin, the rotating handle 14 is turned to drive the threaded rod 13 to rotate in the threaded seat 12, raising the sealing plate 15 and separating it from the bottom inner wall of the sealing gasket 16. The volume of the cavity structure increases, the pressure difference with atmospheric pressure increases, and the sealing gasket 16 is adsorbed and installed on the outer wall of the launch vehicle cabin.

[0045] By adjusting the slide rail 30, the cargo bag 20 is placed at a suitable position below the target falling outside the launch vehicle cabin, and the target falling outside the launch vehicle cabin is caught through the opening at the top of the cargo bag 20.

[0046] During use, the gravity sensor 41 in the fixed connector 10 converts the gravity signal received from the fall arrestor into an electrical signal and feeds it back to the processing component 43 via cable 42. The processing component 43 outputs the target pressure as an electrical signal and sends it to the motor 44 via cable 42. The motor 44 drives the internal thread 17 in the threaded seat 12 to rotate, and according to the principle of relative motion, the threaded rod 13 rotates upward, increasing the volume of the cavity structure and the pressure difference between the inside and outside, thus strengthening the adsorption force between the fixed connector 10 and the outer wall of the launch vehicle cabin. When the depth of the cavity structure reaches a critical value, the processing component 43 issues an alarm signal.

[0047] Upon receiving the alarm signal, the falling device is replaced, the rotating handle 14 is rotated in the opposite direction, causing the threaded rod 13 to rotate in the opposite direction in the threaded seat 12, the sealing plate 15 descends, the volume of the cavity structure decreases, the pressure difference with atmospheric pressure decreases, and the sealing gasket 16 is removed from the outer wall of the launch vehicle cabin.

[0048] The beneficial effects of this utility model are:

[0049] Because the outer wall of the launch vehicle cabin is painted and has a certain curvature, traditional wall-mounted devices that rely on air pressure (such as adhesive hooks) are insufficient. Even with increased size, only the contact area increases, leading to increased friction, but not increased adsorption force. This cannot meet the fall prevention requirements during launch vehicle testing operations. This invention comprehensively analyzes the dry environment outside the launch vehicle cabin, studies the structure and components of the outer rocket body, and designs the fixing connectors based on the special structure of the outer wall of the launch vehicle cabin. This design provides greater pressure than traditional wall-mounted devices and allows for automatic pressure adjustment and alerts. It can reliably adsorb onto the outer wall of the launch vehicle cabin and meet the requirements for periodic replacement. Combined with the special structure of the cargo bag and slide rail, it enables unmanned fall prevention measures outside the cabin, significantly improving the utilization rate of onboard operators in main operation positions, improving the efficiency of onboard testing operations to a certain extent, reducing the operational risks for onboard operators, and enhancing the reliability of rocket launch missions. Attached Figure Description

[0050] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments.

[0051] Figure 1 This is a schematic front view of a fall protection device for external testing operations of a launch vehicle, provided in one embodiment of this utility model.

[0052] Figure 2 This is a top view schematic diagram of a fall protection device for external testing operations of a launch vehicle, provided in one embodiment of this utility model.

[0053] Figure 3This is a schematic diagram of a fixed connector provided in one embodiment of the present invention.

[0054] Figure 4 This is a schematic diagram of a cargo bag provided in one embodiment of the present invention.

[0055] Figure 5 This is a cross-sectional schematic diagram of the locking device in the slide rail provided in one embodiment of the present invention.

[0056] Figure 6 This is a schematic diagram of a pressure regulating device provided in an embodiment of the present invention.

[0057] Figure 7 This is a schematic diagram showing the positions of the processing components and motor in a pressure regulating device provided in an embodiment of this utility model. Detailed Implementation

[0058] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of 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 should fall within the protection scope of the present invention.

[0059] Example 1

[0060] like Figure 1-7 As shown, this utility model provides a fall protection device for external test operations of a launch vehicle, including a fixed connector 10, a cargo bag 20 and a slide rail 30;

[0061] The fixed connector 10 has a cavity structure inside; the fixed connector 10 is installed below the target falling outside the launch vehicle cabin by increasing the volume of the cavity structure and increasing the pressure difference with atmospheric pressure.

[0062] The carrying bag 20 includes a shape expansion member 21 and a load-bearing member 22; the shape expansion member 21 is connected to the top of the load-bearing member 22, and the shape expansion forms an adjustable opening of the carrying bag 20; the bottom of the load-bearing member 22 is sealed, forming the carrying part of the carrying bag 20.

[0063] The shape extension component 21 is made of a material that can deform and has a certain degree of hardness, and can be extended into the target shape according to mission requirements; the load-bearing component 22 is made of a soft material that is not easily scratched, and is used to catch falling targets outside the launch vehicle cabin.

[0064] The slide rail 30 includes a pulley 31 and a track 32. The pulley 31 includes a spherical portion and an extension portion, which are integrally formed. The track 32 has a slide 322, which is adapted to the shape of the spherical portion.

[0065] The pulley 31 is fixed to the opening of the cargo bag 20; the track 32 is installed around the outer wall of the housing 11 of the fixed connector 10; the pulley 31 enters the track 32, the extension extends out of the outside of the slide 322, and the spherical part slides along the slide 322 to adjust the direction and angle of the cargo bag 20, and then catches the falling target outside the launch vehicle cabin.

[0066] Furthermore, the number of fixed connectors 10 corresponds to the number of slide rails 30, and includes at least two.

[0067] The fixed connector 10 includes a housing 11, a threaded seat 12, a threaded rod 13, a rotating handle 14, a sealing plate 15, and a sealing gasket 16; wherein the thread dimensions of the threaded seat 12 and the threaded rod 13 meet the tolerance matching requirements.

[0068] The housing 11 is a cavity structure with an open bottom, and the outer wall of the housing 11 has a mounting groove for the track 32;

[0069] The threaded seat 12 passes through and is fixed at the top center of the housing 11;

[0070] The rotating handle 14 and the sealing plate 15 are respectively installed at both ends of the threaded rod 13;

[0071] After the threaded rod 13 passes through the threaded through hole of the threaded seat 12 through the external thread, the rotating handle 14 is placed on the outside of the housing 11, and the sealing plate 15 is built into the cavity structure of the housing 11, so the edge of the sealing plate 15 is in close contact with the inner wall of the cavity structure.

[0072] The sealing gasket 16 is installed at the bottom edge of the housing 11 but is not completely sealed, preventing the sealing plate 15 from extending out of the bottom of the housing 11;

[0073] When the fixed connector 10 is in use, the sealing plate 15 is tightly attached to the bottom inner wall of the sealing gasket 16; below the target outside the launch vehicle cabin, after the bottom outer wall of the sealing gasket 16 is tightly attached to the outer wall of the launch vehicle cabin, the rotating handle 14 is turned to drive the threaded rod 13 to rotate in the threaded seat 12, raising the sealing plate 15 and separating it from the bottom inner wall of the sealing gasket 16. The volume of the cavity structure increases, the pressure difference with atmospheric pressure increases, and the sealing gasket 16 is adsorbed and installed on the outer wall of the launch vehicle cabin.

[0074] When the fixed connector 10 is replaced, the rotating handle 14 is rotated in the opposite direction, which drives the threaded rod 13 to rotate in the opposite direction in the threaded seat 12. The sealing plate 15 descends, the volume of the cavity structure decreases, the pressure difference with atmospheric pressure decreases, and the sealing gasket 16 is removed from the outer wall of the launch vehicle cabin.

[0075] The sealing gasket 16 is designed with deformable material and is covered with anti-slip rubber.

[0076] The design formula for the fixed connector 10 is as follows:

[0077]

[0078] Wherein, G1 is the weight borne by a single fixed connector 10, G0 is the weight of a single fixed connector 10 itself, μ is the coefficient of friction between the fall arrestor and the outer wall of the launch vehicle cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing gasket 16, S0 is the area of ​​the bottom of the shell 11 that is not completely sealed, h1 is the height of the upward rotation of the threaded rod 13, the maximum value of h1 is the depth of the cavity structure, S1 is the contact area between the fall arrestor and the launch vehicle (generally the area of ​​the circle with a radius of circumference outside the sealing gasket), and θ is the angle between the installation position of the fall arrestor and the horizontal plane, θ is 0 to 90°.

[0079] Furthermore, the fixed connector 10 has a built-in pressure regulating device that increases the volume of the cavity structure; the pressure regulating device includes a gravity sensor 41, a processing component 43, and a motor 44;

[0080] The gravity sensor 41 is built into the sealing gasket 16, the processing component 43 is built into the threaded seat 12, and the motor 44 is embedded in the threaded seat 12 and fixedly connected to the internal thread 17; the gravity sensor 41 is connected to the processing component 43 through the cable 42, and the processing component 43 is connected to the motor 44 through the cable 42.

[0081] The gravity sensor 41 converts the received gravity signal from the fall arrestor into an electrical signal and feeds it back to the processing component 43 via cable 42. The processing component 43 outputs the obtained target pressure as an electrical signal and sends it to the motor 44 via cable 42. The motor 44 drives the internal thread 17 in the threaded seat 12 to rotate, causing the threaded rod 13 to rotate upward according to the principle of relative motion. The volume of the cavity structure increases, the pressure difference between the inside and outside increases, and the adsorption force between the fixed connector 10 and the outer wall of the launch vehicle cabin increases. When the depth of the cavity structure reaches the critical value, the processing component 43 issues an alarm signal to prompt the replacement of the fall arrestor.

[0082] Among them, the gravity sensor models can be BMA253, XSCB-50kg or XSGB-50kg, etc.

[0083] The processing unit can be an 8051 microcontroller, a PIC microcontroller, or an MSP430 microcontroller, etc.

[0084] The motors that can be selected are: ZYT AC motor, RF-300CA DC motor or N20 DC motor, etc.

[0085] The formula for calculating the target pressure obtained by the processing component 43 is as follows:

[0086]

[0087] Wherein, G1 is the weight borne by a single fixed connector 10, G0 is the weight of a single fixed connector 10 itself, μ is the coefficient of friction between the fall arrestor and the outer wall of the launch vehicle cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing gasket 16, S0 is the area of ​​the bottom of the shell 11 that is not completely sealed, h1 is the height of the threaded rod 13 rotating upward, the maximum value of h1 is the depth of the cavity structure, S1 is the contact area between the fall arrestor and the launch vehicle, and θ is the angle between the installation position of the fall arrestor and the horizontal plane, θ is 0 to 90°.

[0088] Furthermore, the slide rail 30 has a locking device;

[0089] The locking device includes a locking part disposed on the pulley 31 and at least one limiting groove 321 disposed in the slide rail 322;

[0090] The locking part is placed into the corresponding limiting groove to lock the relative position of the pulley 31 on the track 32; after the locking part is moved out of the limiting groove, the pulley 31 slides in the track 32.

[0091] Furthermore, the locking part includes a locking unit disposed on the spherical part and an unlocking unit disposed on the extension part;

[0092] The unlocking unit includes an unlocking button 311, an unlocking spring 312, and an unlocking slider 313; the lower end of the unlocking button 311 is built into the extension, and the bottom end is connected to the top end of the unlocking spring 312, and the bottom end of the unlocking spring 312 is connected to the top end of the unlocking slider 313.

[0093] The locking unit includes a locking slide 315, a locking spring 316, and a locking key 317, wherein the locking key 317 is adapted to the shape of the limiting groove 321; the lower end of the locking key 317 is built into the spherical part, the bottom end is connected to the top end of the locking slide 315, and the bottom end of the locking slide 315 is connected to the locking spring 316.

[0094] The locking slide 315 and the unlocking slide 313 are connected by a hinge on the connecting rod 314;

[0095] The elastic coefficient of the locking spring 316 is greater than that of the unlocking spring 312. When no external force is applied to the unlocking button 311, the unlocking spring 312 is in a naturally extended state and the locking spring 316 is in a naturally compressed state. At this time, the locking key 317 pops up and gets into the limiting groove 321 to achieve the locking state.

[0096] When a pulling force is applied to the unlock button 311, the unlock spring 312 is in a stretched state, the unlock slider 313 moves upward, causing the connecting rod 314 to rotate, the locking slider 315 moves downward, causing the locking key 317 to move downward, the locking spring 316 is compressed, and the locking key 317 disengages from the limiting groove 321, thus achieving the unlocked state.

[0097] The locking device is used to fix the relative positions of the pulley and the track, preventing the fixed connector and the cargo bag from sliding relative to each other during use, thus ensuring reliable operation.

[0098] Furthermore, one or more of the cargo bags 20 are used for nesting;

[0099] There is a gap between the stacked cargo bags 20, and the volume of the lower stacked cargo bag 20 is larger than that of the current cargo bag 20. This prevents the primary protection provided by the current cargo bag 20 from exceeding the maximum gravity bearing capacity and falling, or from scattering the falling target. The lower stacked cargo bag 20 then catches the target, thus achieving secondary protection.

[0100] The working principle and process of this utility model include:

[0101] As needed, wipe the installation location of the fall arrestor below the target outside the launch vehicle compartment;

[0102] The sealing plate 15 of the fixed connector 10 is tightly attached to the bottom inner wall of the sealing gasket 16; below the target outside the launch vehicle cabin, after the bottom outer wall of the sealing gasket 16 is tightly attached to the outer wall of the launch vehicle cabin, the rotating handle 14 is turned to drive the threaded rod 13 to rotate in the threaded seat 12, raising the sealing plate 15 and separating it from the bottom inner wall of the sealing gasket 16. The volume of the cavity structure increases, the pressure difference with atmospheric pressure increases, and the sealing gasket 16 is adsorbed and installed on the outer wall of the launch vehicle cabin.

[0103] By adjusting the slide rail 30, the cargo bag 20 is placed at a suitable position below the target falling outside the launch vehicle cabin, and the target falling outside the launch vehicle cabin is caught through the opening at the top of the cargo bag 20.

[0104] During use, the gravity sensor 41 in the fixed connector 10 converts the gravity signal received from the fall arrestor into an electrical signal and feeds it back to the processing component 43 via cable 42. The processing component 43 outputs the target pressure as an electrical signal and sends it to the motor 44 via cable 42. The motor 44 drives the internal thread 17 in the threaded seat 12 to rotate, and according to the principle of relative motion, the threaded rod 13 rotates upward, increasing the volume of the cavity structure and the pressure difference between the inside and outside, thus strengthening the adsorption force between the fixed connector 10 and the outer wall of the launch vehicle cabin. When the depth of the cavity structure reaches a critical value, the processing component 43 issues an alarm signal.

[0105] Upon receiving the alarm signal, the falling device is replaced, the rotating handle 14 is rotated in the opposite direction, causing the threaded rod 13 to rotate in the opposite direction in the threaded seat 12, the sealing plate 15 descends, the volume of the cavity structure decreases, the pressure difference with atmospheric pressure decreases, and the sealing gasket 16 is removed from the outer wall of the launch vehicle cabin.

[0106] Based on the above working principle and process, specific examples are provided to illustrate the technical solution of this utility model in detail:

[0107] Table 1

[0108] 1 323.4N 0.49 101325Pa 90° 0.08m 0.01m <![CDATA[π0.05 2 m 2 ]]> <![CDATA[π0.03 2 m 2 ]]> 49N 2 322.9N 0.49 101325Pa 90° 0.05m 0.01m <![CDATA[π0.05 2 m 2 ]]> <![CDATA[π0.03 2 m 2 ]]> 39N

[0109] In Example 1, a single fixed connector can withstand a weight of 323.4 N, or 33 kg (g = 9.8 m / s²). 2 );

[0110] In Example 2, a single fixed connector can withstand a weight of 322.9 N, or 32.95 kg (g = 9.8 m / s²). 2 ).

[0111] The beneficial effects of this utility model are:

[0112] Because the outer wall of the launch vehicle cabin is painted and has a certain curvature, traditional wall-mounted devices that rely on air pressure (such as adhesive hooks) are insufficient. Even with increased size, only the contact area increases, leading to increased friction, but not increased adsorption force. This cannot meet the fall prevention requirements during launch vehicle testing operations. This invention comprehensively analyzes the dry environment outside the launch vehicle cabin, studies the structure and components of the outer rocket body, and designs the fixing connectors based on the special structure of the outer wall of the launch vehicle cabin. This design provides greater pressure than traditional wall-mounted devices and allows for automatic pressure adjustment and alerts. It can reliably adsorb onto the outer wall of the launch vehicle cabin and meet the requirements for periodic replacement. Combined with the special structure of the cargo bag and slide rail, it enables unmanned fall prevention measures outside the cabin, significantly improving the utilization rate of onboard operators in main operation positions, improving the efficiency of onboard testing operations to a certain extent, reducing the operational risks for onboard operators, and enhancing the reliability of rocket launch missions.

[0113] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. A fall arrest device for use in an external test operation of a launch vehicle, characterized by, Includes fixed connectors, cargo bags, and slide rails; The fixed connector has an internal cavity structure; the fixed connector is installed below the target falling outside the launch vehicle cabin by increasing the volume of the cavity structure and increasing the pressure difference with atmospheric pressure. The carrying bag includes a shape-expanding component and a load-bearing component; the top of the shape-expanding component is connected to the top of the load-bearing component, and the shape-expanding component forms an adjustable opening for the carrying bag; the bottom of the load-bearing component is sealed, forming the carrying part of the carrying bag. The slide rail includes a pulley and a track. The pulley includes a spherical portion and an extension portion, which are integrally formed. The track has a slide path that is adapted to the shape of the spherical portion. The pulley is fixed to the opening of the cargo bag; the track is installed around the outer wall of the housing of the fixed connector; the pulley enters the track, the extension extends out of the outside of the slide, and the spherical part slides along the slide to adjust the direction and angle of the cargo bag before catching the falling target outside the launch vehicle cabin.

2. The fall arrest device for use in an orbital test operation of a launch vehicle according to claim 1, characterized in that The number of fixed connectors corresponds to the number of slide rails, and includes at least two.

3. The fall arrest device for use in an orbital test operation of a launch vehicle according to claim 2, characterized in that The fixed connector includes a housing, a threaded seat, a threaded rod, a rotary handle, a sealing plate, and a sealing gasket; wherein the thread dimensions of the threaded seat and the threaded rod meet the tolerance matching requirements; The housing is a hollow structure with an open bottom, and the outer wall of the housing has a mounting groove for the track; The threaded seat passes through and is fixed at the top center of the housing; The rotating handle and the sealing plate are respectively installed at both ends of the threaded rod; After the threaded rod passes through the threaded through hole of the threaded seat through the external thread, the rotating handle is placed on the outside of the housing, and the sealing plate is built into the cavity structure of the housing, so the edge of the sealing plate is in close contact with the inner wall of the cavity structure. The sealing gasket is installed at the bottom edge of the housing but is not completely sealed, preventing the sealing plate from extending out of the bottom of the housing.

4. The fall arrest device for use in an orbital test operation of a launch vehicle according to claim 3, characterized in that The sealing gasket is designed with deformable material and is covered with anti-slip rubber.

5. The fall arrest device for use in an orbital test operation of a launch vehicle according to claim 4, characterized in that The design formula for the fixed connector is: ； Wherein, G1 is the weight borne by a single fixed connector, G0 is the weight of a single fixed connector itself, μ is the coefficient of friction between the fall arrestor and the outer wall of the launch vehicle cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing gasket, S0 is the area of ​​the bottom of the shell that is not completely sealed, h1 is the height of the threaded rod rotating upward, the maximum value of h1 is the depth of the cavity structure, S1 is the contact area between the fall arrestor and the launch vehicle, and θ is the angle between the installation position of the fall arrestor and the horizontal plane, θ is 0~90°.

6. The fall arrest device for use in an orbital test operation of a launch vehicle according to claim 5, characterized in that The fixed connector has a built-in pressure regulating device that increases the volume of the cavity structure; the pressure regulating device includes a gravity sensor, processing components, and a motor. The gravity sensor is built into a sealing gasket, the processing component is built into a threaded seat, and the motor is embedded in the threaded seat and fixedly connected to the internal thread; the gravity sensor is connected to the processing component via a cable, and the processing component is connected to the motor via a cable. The gravity sensor converts the gravity signal received from the fall arrestor into an electrical signal and feeds it back to the processing component via a cable. The processing component outputs the target pressure as an electrical signal and sends it to the motor via a cable. The motor drives the internal thread in the threaded seat to rotate, and according to the principle of relative motion, the threaded rod rotates upward, increasing the volume of the cavity structure and the pressure difference between the inside and outside. This strengthens the adhesion between the fixed connector and the outer wall of the launch vehicle cabin. When the depth of the cavity structure reaches a critical value, the processing component issues an alarm signal, prompting the replacement of the fall arrestor.

7. The fall arrest device for use in an orbital test operation of a launch vehicle according to claim 6, characterized in that The formula for calculating the target pressure obtained by the processing components is as follows: ； Wherein, G1 is the weight borne by a single fixed connector, G0 is the weight of a single fixed connector itself, μ is the coefficient of friction between the fall arrestor and the outer wall of the launch vehicle cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing gasket, S0 is the area of ​​the bottom of the shell that is not completely sealed, h1 is the height of the threaded rod rotating upward, the maximum value of h1 is the depth of the cavity structure, S1 is the contact area between the fall arrestor and the launch vehicle, and θ is the angle between the installation position of the fall arrestor and the horizontal plane, θ is 0~90°.

8. The fall arrest device for use in an orbital test operation of a launch vehicle according to claim 1, wherein, The slide rail has a locking device; The locking device includes a locking part disposed on the pulley and at least one limiting groove disposed in the slide rail; The locking part is placed into the corresponding limiting groove to lock the relative position of the pulley on the track; after the locking part is moved out of the limiting groove, the pulley slides in the track.

9. The fall arrest device for use in an orbital test operation of a launch vehicle according to claim 8, characterized in that The locking part includes a locking unit disposed on the spherical part and an unlocking unit disposed on the extension part; The unlocking unit includes an unlocking button, an unlocking spring, and an unlocking slider; the lower end of the unlocking button is built into the extension, and the bottom end is connected to the top end of the unlocking spring, and the bottom end of the unlocking spring is connected to the top end of the unlocking slider. The locking unit includes a locking slide, a locking spring, and a locking key, wherein the locking key is adapted to the shape of the limiting groove; the lower end of the locking key is built into the spherical part, the bottom end is connected to the top end of the locking slide, and the bottom end of the locking slide is connected to the locking spring; The locking slider and the unlocking slider are connected by a hinge on the connecting rod; The spring constant of the locking spring is greater than that of the unlocking spring. When no external force is applied to the unlocking button, the unlocking spring is in a naturally extended state and the locking spring is in a naturally compressed state. At this time, the locking button pops up and gets into the limiting groove to achieve the locking state.

10. The fall arrest device for use in an orbital test operation of a launch vehicle according to one of claims 1 to 9, characterized in that The cargo bags are stacked using one or more nested together. There are gaps between the nested bags, and the volume of the nested bags in the lower layer is larger than that of the current layer.

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