Anti-falling device for outboard test operation of carrier rocket

Abstract

The invention provides an anti-falling device for outboard test operation of a carrier rocket, belongs to the field of carrier rockets, and solves the problem of how to realize unmanned outboard anti-falling measures. Comprising a fixed connecting piece, a carrying bag and a sliding rail; a cavity structure is arranged in the fixed connecting piece; by increasing the volume of the cavity structure and increasing the pressure difference with the atmospheric pressure, the device is adsorbed and mounted below a falling target outside a carrier rocket cabin; the sliding rail comprises a pulley and a track, the pulley comprises a spherical part and an extension part, and the spherical part and the extension part are integrally formed; the slideway of the track is matched with the spherical part in shape; the pulley is fixed at the opening part of the carrying bag; the track is installed on the outer wall of the shell of the fixed connecting piece in a surrounding mode. The pulleys enter the rails, the extending parts extend out of the outer sides of the sliding ways, and the spherical parts slide along the sliding ways to adjust the direction and angle of the carrying bag and then catch a falling target outside the carrier rocket cabin; according to the invention, unmanned anti-falling measures outside the cabin are realized, and the operation risk is reduced.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of carrier rockets, and particularly relates to a falling prevention device for carrier rocket extravehicular test operation. BACKGROUND

[0002] The test of a carrier rocket at a space launch site and an assembly plant involves many extravehicular operation work items, and during the extravehicular test operation of the carrier rocket, excess objects may fall onto the extravehicular operation platform of the carrier rocket, which brings great safety hazards to the extravehicular operation platform of the carrier rocket and the extravehicular test operation personnel on the platform.

[0003] At present, the falling prevention measures of the extravehicular test operation system of the carrier rocket all need manual assistance, which, although solves the safety hazards to some extent, also leads to the fact that the extravehicular test operation work of the carrier rocket cannot be completed independently by a single person, thereby affecting the work efficiency.

[0004] Therefore, the falling prevention device without manual assistance is very important during the extravehicular test operation of the carrier rocket, which can ensure the safety of the extravehicular environment of the carrier rocket, reduce the operation risk, and improve the work efficiency of the extravehicular test operation personnel of the carrier rocket. Therefore, a falling prevention device for extravehicular test operation of a carrier rocket is urgently needed. SUMMARY

[0005] In order to solve the problems of how to reduce the operation risk of the extravehicular test operation of the carrier rocket and improve the work efficiency of the extravehicular test operation personnel of the carrier rocket, based on the special drying structure that the extravehicular wall of the carrier rocket is painted and has a certain arc, the present application provides a falling prevention device for extravehicular test operation of a carrier rocket, which realizes the unmanned extravehicular falling prevention measure through the connecting structure of the fixed connecting piece, the object carrying bag and the sliding rail, effectively reduces the operation risk of the extravehicular operation personnel, and improves the work efficiency of the extravehicular test operation personnel of the carrier rocket.

[0006] To achieve the above purpose, the present application is realized by the following technical scheme:

[0007] The present application provides a falling prevention device for extravehicular test operation of a carrier rocket, which comprises a fixed connecting piece 10, an object carrying bag 20 and a sliding rail 30.

[0008] The fixed connecting piece 10 has a cavity structure inside; the fixed connecting piece 10 increases the volume of the cavity structure, increases the pressure difference with the atmospheric pressure, and adsorbs the falling target below the extravehicular operation platform of the carrier rocket;

[0009] The load bag 20 includes a shape expanding part 21 and a force bearing part 22; the shape expanding part 21 is connected with the top of the force bearing part 22, and forms an opening part with adjustable shape of the load bag 20 by shape expanding; the bottom of the force bearing part 22 is sealed, and forms a load part of the load bag 20;

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

[0011] The pulley 31 is fixed at the opening part of the load bag 20; the track 32 is installed around the outer wall of the shell 11 of the fixed connecting part 10; the pulley 31 enters the track 32, the extension part extends out of the outer side of the slide channel 322, and the spherical part slides along the slide channel 322 to adjust the direction and angle of the load bag 20, and then catches the falling target outside the cabin of the carrier rocket.

[0012] Further, the number of the fixed connecting part 10 and the slide rail 30 corresponds, and at least two.

[0013] The fixed connecting part 10 includes a shell 11, a threaded seat 12, a threaded rod 13, a rotating handle 14, a sealing plate 15 and a sealing gasket 16; the threaded size of the threaded seat 12 and the threaded rod 13 meets the tolerance matching requirement;

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

[0015] The threaded seat 12 penetrates and is fixed at the top center position of the shell 11;

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

[0017] The threaded rod 13 penetrates the threaded through hole of the threaded seat 12 through external threads, and then places the rotating handle 14 outside the shell 11, and simultaneously embeds the sealing plate 15 in the cavity structure of the shell 11, so that the edge of the sealing plate 15 closely abuts the inner wall of the cavity structure;

[0018] The sealing gasket 16 is sealingly installed at the bottom edge of the shell 11 and does not completely seal, and blocks the sealing plate 15 from extending out of the bottom of the shell 11;

[0019] The fixed connecting piece 10 is used to tightly seal the bottom inner wall of the sealing plate 15 and the bottom outer wall of the sealing pad 16. When the carrying rocket cabin falls below the target, the sealing plate 15 is lifted by rotating the rotating handle 14 to separate the sealing plate 15 from the bottom inner wall of the sealing pad 16, so that the volume of the cavity structure increases and the pressure difference of the atmospheric pressure increases. The sealing pad 16 is adsorbed and installed on the outer wall of the carrying rocket cabin.

[0020] When the fixed connecting piece 10 is replaced, the rotating handle 14 is reversely rotated to drive the threaded rod 13 to reversely rotate in the threaded seat 12, so that the sealing plate 15 is lowered, the volume of the cavity structure is reduced, the pressure difference of the atmospheric pressure is reduced, and the sealing pad 16 is removed from the outer wall of the carrying rocket cabin.

[0021] The sealing pad 16 is designed of a deformation material and is coated with anti-skid rubber.

[0022] The design formula of the fixed connecting piece 10 is as follows:

[0023]

[0024] G1 is the gravity borne by a single fixed connecting piece 10, G0 is the gravity of a single fixed connecting piece 10, μ is the friction coefficient between the anti-falling device and the outer wall of the carrying rocket cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing pad 16, S0 is the incomplete sealing area of the bottom of the shell 11, h1 is the upward rotation height of the threaded rod 13, the maximum value of h1 is the depth of the cavity structure, S1 is the contact area between the anti-falling device and the carrying rocket, and θ is the angle between the installation position of the anti-falling device and the horizontal plane, which is 0-90°.

[0025] Further, the fixed connecting piece 10 is provided with a pressure adjusting device for increasing the volume of the cavity structure; the pressure adjusting device comprises a gravity sensor 41, a processing component 43 and a motor 44.

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

[0027] The gravity sensor 41 converts the received gravity signal of the anti-falling device into an electrical signal, which is fed back to the processing element 43 through the cable 42. The processing element 43 outputs the target pressure as an electrical signal to the motor 44 through the cable 42. The motor 44 drives the internal thread 17 in the threaded seat 12 to rotate, which makes the threaded rod 13 rotate upward according to the principle of relative motion, increases the volume of the cavity structure, and increases the pressure difference between the inside and outside. The adsorption force between the fixed connecting piece 10 and the outer wall of the carrier rocket cabin is enhanced; when the depth of the cavity structure reaches the critical value, the processing element 43 sends an alarm signal to prompt the replacement of the anti-falling device.

[0028] The calculation formula of the target pressure obtained by the processing element 43 is:

[0029]

[0030] Wherein, G1 is the gravity borne by a single fixed connecting piece 10, G0 is the gravity of a single fixed connecting piece 10 itself, μ is the friction coefficient between the anti-falling device and the outer wall of the carrier rocket cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing gasket 16, S0 is the area of the incomplete seal at the bottom of the shell 11, 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 anti-falling device and the carrier rocket, and θ is the angle between the installation position of the anti-falling device and the horizontal plane, θ is 0-90°.

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

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

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

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

[0035] The unlocking unit includes an unlocking knob 311, an unlocking spring 312 and an unlocking slide 313; the lower end of the unlocking knob 311 is built into the extension part, the bottom end is connected with the top end of the unlocking spring 312, and the bottom end of the unlocking spring 312 is connected with the top end of the unlocking slide 313;

[0036] The locking unit comprises a locking slide 315, a locking spring 316 and a locking key 317, wherein the locking key 317 is matched with the shape of the limiting groove 321; the lower end of the locking key 317 is built in the spherical part, the bottom end is connected with the top end of the locking slide 315, and the bottom end of the locking slide 315 is connected with the locking spring 316;

[0037] The locking slide 315 and the unlocking slide 313 are connected through the 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 knob 311, the unlocking spring 312 is in a natural elongation state, and the locking spring 316 is in a natural compression state, at this time, the locking key 317 is popped up and clamped into the limiting groove 321, so that the locking state is realized;

[0039] When a pulling force is applied to the unlocking knob 311, the unlocking spring 312 is in a stretching state, the unlocking slide 313 moves upwards, the connecting rod 314 rotates, the locking slide 315 moves downwards, the locking key 317 moves downwards, the locking spring 316 is compressed, the locking key 317 is separated from the limiting groove 321, and the unlocking state is realized.

[0040] Further, the object carrying bag 20 is nested by one or more;

[0041] The nested object carrying bags 20 are left with gaps, and the volume of the lower layer nested object carrying bag 20 is greater than that of the current layer object carrying bag 20.

[0042] The working principle and process of the application include:

[0043] According to the needs, the installation position of the anti-falling device is wiped under the falling target outside the launch vehicle cabin;

[0044] The sealing plate 15 of the fixed connecting piece 10 is tightly attached to the bottom inner wall of the sealing pad 16; after the bottom outer wall of the sealing pad 16 is tightly attached to the outer wall of the launch vehicle cabin, the rotating handle 14 is rotated, the threaded rod 13 is rotated in the threaded seat 12, the sealing plate 15 is lifted, and the sealing plate 15 is separated from the bottom inner wall of the sealing pad 16, the volume of the cavity structure is increased, the pressure difference of the atmospheric pressure is increased, and the sealing pad 16 is adsorbed and installed on the outer wall of the launch vehicle cabin;

[0045] The object carrying bag 20 is placed in a suitable position under the falling target outside the launch vehicle cabin through the adjustment of the sliding rail 30, and the falling target outside the launch vehicle cabin is caught through the opening part at the top end of the object carrying bag 20;

[0046] During use, the gravity sensor 41 in the fixed connecting piece 10 converts the received gravity signal of the anti-falling device into an electric signal, which is fed back to the processing element 43 through the cable 42, the processing element 43 outputs the derived target pressure as an electric signal to the motor 44 through the cable 42, the motor 44 drives the internal thread 17 in the threaded seat 12 to rotate, according to the principle of relative motion, the threaded rod 13 is rotated upward, the volume of the cavity structure is increased, the pressure difference between the internal and external pressures is changed, and the adsorption force between the fixed connecting piece 10 and the outer wall of the launch vehicle cabin is increased; when the depth of the cavity structure reaches a critical value, the processing element 43 sends an alarm signal;

[0047] After receiving the alarm signal, the falling device is replaced, the rotary handle 14 is rotated in the reverse direction, the threaded rod 13 is reversely rotated in the threaded seat 12, the sealing plate 15 is lowered, the volume of the cavity structure is reduced, the pressure difference with the atmospheric pressure is reduced, and the sealing gasket 16 is removed from the outer wall of the launch vehicle cabin.

[0048] The beneficial effects of the present application are:

[0049] Because the outer wall of the launch vehicle cabin is coated with paint and has a certain curvature, the traditional wall-mounted device (such as a hook) relying on air pressure is insufficient in pressure, even if the volume is increased, only the contact area is increased, resulting in an increase in friction, but no increase in adsorption force, which cannot meet the requirements of anti-falling in the launch vehicle test operation, the present application comprehensively analyzes the dry environment outside the cabin of the launch vehicle, studies the structure and components of the rocket body outside the cabin, and combines the special structure of the outer wall of the launch vehicle cabin to design the fixed connecting piece, which has greater pressure than the traditional wall-mounted device, and can automatically adjust and prompt the pressure, and can realize reliable adsorption and regular replacement of the outer wall of the launch vehicle cabin, combined with the special structure of the load bag and the slide rail, the unmanned anti-falling measure outside the cabin can be realized, the utilization rate of the on-rocket operation personnel participating in the main operation post is greatly improved, the efficiency of the on-rocket test operation is improved to a certain extent, the operation risk of the on-rocket operation personnel is reduced, and the reliability of the rocket launch task is improved. BRIEF DESCRIPTION OF DRAWINGS

[0050] The present application will be further described in detail below according to the drawings and examples.

[0051] Figure 1 is a front view schematic diagram of an anti-falling device for launch vehicle cabin test operation provided by an embodiment of the present application.

[0052] Figure 2 is a top view schematic diagram of an anti-falling device for launch vehicle cabin test operation provided by an embodiment of the present application.

[0053] Figure 3 is a schematic diagram of a fixed connecting piece provided by an embodiment of the present application.

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

[0055] Figure 5 This is a cross-sectional schematic diagram of a locking device in a slide rail according to an 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 the present invention. 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 of the present invention. 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 scope of protection of the present invention.

[0059] Example 1

[0060] like Figures 1-7 As shown, the present invention 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 at the opening of the object bag 20; the track 32 is installed around the outer wall of the shell 11 of the fixed connecting piece 10; the pulley 31 enters the track 32, the extension part extends out of the outer side of the slide 322, and the spherical part slides along the slide 322 to adjust the direction and angle of the object bag 20, and then catches the falling target outside the launch vehicle cabin.

[0066] Further, the number of the fixed connecting piece 10 and the slide rail 30 corresponds to at least two.

[0067] The fixed connecting piece 10 comprises a shell 11, a threaded seat 12, a threaded rod 13, a rotating handle 14, a sealing plate 15 and a sealing gasket 16; wherein the threaded size of the threaded seat 12 and the threaded rod 13 meets the tolerance matching requirement.

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

[0069] The threaded seat 12 penetrates and is fixed at the top center position of the shell 11;

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

[0071] The threaded rod 13 penetrates the threaded through hole of the threaded seat 12 through the external thread, and then the rotating handle 14 is placed outside the shell 11, and the sealing plate 15 is placed inside the cavity structure of the shell 11, so that the edge of the sealing plate 15 closely abuts the inner wall of the cavity structure;

[0072] The sealing gasket 16 is sealingly installed at the bottom edge of the shell 11 and does not completely seal, and blocks the sealing plate 15 from extending out of the bottom of the shell 11;

[0073] When the fixed connecting piece 10 is used, the sealing plate 15 closely abuts the inner wall of the bottom of the sealing gasket 16; after the outer wall of the bottom of the sealing gasket 16 is closely abutted with the outer wall of the launch vehicle cabin below the falling target outside the launch vehicle cabin, the rotating handle 14 is rotated to drive the threaded rod 13 to rotate in the threaded seat 12, the sealing plate 15 is raised to separate from the inner wall of the bottom of the sealing gasket 16, the volume of the cavity structure is increased, the pressure difference with the atmospheric pressure is increased, and the sealing gasket 16 is adsorbed and installed on the outer wall of the launch vehicle cabin.

[0074] When the fixed connecting piece 10 is replaced, the rotating handle 14 is reversely rotated to drive the threaded rod 13 to reversely rotate in the threaded seat 12, the sealing plate 15 is lowered, the volume of the cavity structure is reduced, the pressure difference with the atmospheric pressure is reduced, and the sealing gasket 16 is removed from the outer wall of the launch vehicle cabin.

[0075] The sealing gasket 16 is designed of deformable material and is coated with anti-skid rubber.

[0076] The design formula of the fixed connecting piece 10 is:

[0077]

[0078] G1 is the gravity borne by a single fixed connecting piece 10, G0 is the gravity of a single fixed connecting piece 10 itself, μ is the friction coefficient between the anti-falling device 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 which 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 anti-falling device and the launch vehicle (generally the area of a circle with the radius of the circumference of the sealing gasket), and θ is the angle between the installation position of the anti-falling device and the horizontal plane, θ is 0-90°.

[0079] Further, the fixed connecting piece 10 is internally provided with a pressure adjusting device for increasing the volume of the cavity structure; the pressure adjusting device comprises a gravity sensor 41, a processing element 43 and a motor 44.

[0080] The gravity sensor 41 is internally provided in the sealing gasket 16, the processing element 43 is internally provided in the threaded seat 12, and the motor 44 is embedded in the threaded seat 12 and fixedly connected with the internal thread 17; the gravity sensor 41 is connected with the processing element 43 through a cable 42, and the processing element 43 is connected with the motor 44 through the cable 42.

[0081] The gravity sensor 41 converts the received gravity signal of the anti-falling device into an electric signal and feeds back the electric signal to the processing element 43 through the cable 42, the processing element 43 outputs the obtained target pressure as an electric signal to the motor 44 through the cable 42, the motor 44 drives the internal thread 17 in the threaded seat 12 to rotate, according to the principle of relative motion, the threaded rod 13 is rotated upward, the volume of the cavity structure is increased, the pressure difference between the inside and outside is increased, and the adsorption force between the fixed connecting piece 10 and the outer wall of the launch vehicle cabin is increased; when the depth of the cavity structure reaches a critical value, the processing element 43 sends an alarm signal to prompt replacement of the anti-falling device.

[0082] The model of the gravity sensor can be selected from BMA253, XSCB-50kg or XSGB-50kg, etc.

[0083] The processing unit can be selected from 8051 single-chip microcomputer, PIC single-chip microcomputer or MSP430 single-chip microcomputer, etc.

[0084] The motor can be selected from ZYT model AC motor, RF-300CA model DC motor or N20 model DC motor, etc.

[0085] The calculation formula of the target pressure obtained by the processing element 43 is as follows:

[0086]

[0087] Wherein, G1 is the gravity of the single fixed connecting piece 10, G0 is the gravity of the single fixed connecting piece 10 itself, μ is the friction coefficient between the anti-falling device and the outer wall of the carrier rocket cabin, p0 is the local atmospheric pressure, h0 is the depth of the sealing gasket 16, S0 is the area of the incomplete sealing of the bottom of the shell 11, h1 is the upward rotation height of the threaded rod 13, the maximum value of h1 is the depth of the cavity structure, S1 is the contact area of the anti-falling device and the carrier rocket, and θ is the angle between the installation position of the anti-falling device and the horizontal plane, θ is 0-90°.

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

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

[0090] The locking part is put into the corresponding limiting groove, and the relative position of the pulley 31 in the track 32 is locked; after the locking part is moved out of the limiting groove, the pulley 31 slides in the track 32.

[0091] Further, the locking part comprises a locking unit arranged on the spherical part and an unlocking unit arranged on the extension part;

[0092] The unlocking unit comprises an unlocking knob 311, an unlocking spring 312 and an unlocking slide 313; the lower end of the unlocking knob 311 is arranged in the extension part, the bottom end is connected with the top end of the unlocking spring 312, and the bottom end of the unlocking spring 312 is connected with the top end of the unlocking slide 313;

[0093] The locking unit comprises a locking slide 315, a locking spring 316 and a locking key 317, wherein the locking key 317 is matched with the shape of the limiting groove 321; the lower end of the locking key 317 is arranged in the spherical part, the bottom end is connected with the top end of the locking slide 315, and the bottom end of the locking slide 315 is connected with the locking spring 316;

[0094] The locking slide 315 and the unlocking slide 313 are connected through the 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 knob 311, the unlocking spring 312 is in a natural elongation state, and the locking spring 316 is in a natural compression state, at this time the locking key 317 is popped up and clamped into the limiting groove 321, realizing the locking state;

[0096] When pulling force is applied to the unlocking knob 311, the unlocking spring 312 is in a stretched state, the unlocking slide 313 moves upward, the connecting rod 314 rotates, the locking slide 315 moves downward, the locking key 317 moves downward, the locking spring 316 is compressed, the locking key 317 is separated from the limiting groove 321, and the unlocking state is realized.

[0097] The locking device fixes the relative position of the pulley and the track, and allows the fixed connecting piece and the object bag to not slide relative to each other during use, and reliable work is realized.

[0098] Further, the object bag 20 uses one or more to be nested;

[0099] The nested object bags 20 have a gap, and the volume of the lower nested object bag 20 is greater than that of the current layer object bag 20, so that the current object bag 20 does not exceed the maximum bearing gravity and falls or scatters the falling target, and the lower nested object bag 20 is caught to realize secondary protection.

[0100] The working principle and process of the application include:

[0101] According to the need, the installation position of the anti-falling device is wiped under the falling target outside the launch vehicle cabin;

[0102] The sealing plate 15 of the fixed connecting piece 10 is tightly attached to the bottom inner wall of the sealing pad 16; after the bottom outer wall of the sealing pad 16 is tightly attached to the outer wall of the launch vehicle cabin, the rotating handle 14 is rotated, the threaded rod 13 is rotated in the threaded seat 12, the sealing plate 15 is raised, and the sealing plate 15 is separated from the bottom inner wall of the sealing pad 16, the volume of the cavity structure is increased, the pressure difference of the atmospheric pressure is increased, and the sealing pad 16 is adsorbed and installed on the outer wall of the launch vehicle cabin;

[0103] The object bag 20 is placed at a suitable position under the falling target outside the launch vehicle cabin by adjusting the slide rail 30, and the falling target outside the launch vehicle cabin is caught through the opening part at the top end of the object bag 20;

[0104] During use, the gravity sensor 41 in the fixed connecting piece 10 converts the received gravity signal of the anti-falling device into an electric signal, which is fed back to the processing component 43 through the cable 42. The processing component 43 outputs the derived target pressure as an electric signal to the motor 44 through the 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 is rotated upward. The volume of the cavity structure is increased, the pressure difference between the inside and outside is increased, and the adsorption force between the fixed connecting piece 10 and the outer wall of the launch vehicle cabin is increased. When the depth of the cavity structure reaches a critical value, the processing component 43 sends an alarm signal.

[0105] After receiving the alarm signal, the falling device is replaced, the rotary handle 14 is rotated in the opposite direction, the threaded rod 13 is rotated in the opposite direction in the threaded seat 12, the sealing plate 15 is lowered, the volume of the cavity structure is reduced, the pressure difference with the atmospheric pressure is reduced, 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, the technical solutions of the present application are described in detail by providing specific examples:

[0107] Table 1

[0108] Parameter [G1] μ [p0] θ [CDATA[h2]]> [ h0 ] [S1] [S0] [G0] 1 323.4N 0.49 101325 Pa 90° 0.08m 0.01m <![CDATA[π0.05 2 m 2 ]]> <![CDATA[π0.03 2 m 2 ]]> 49N 2 322.9N 0.49 101325 Pa 90° 0.05m 0.01m <![CDATA[π0.05 2 m 2 ]]> <![CDATA[π0.03 2 m 2 ]]> 39N

[0109] In Example 1, the gravity that a single fixed connecting piece can withstand is 323.4N, i.e. 33kg (g is 9.8m / s 2 );

[0110] In Example 2, the gravity that a single fixed connecting piece can withstand is 322.9N, i.e. 32.95kg (g is 9.8m / s 2 )。

[0111] The beneficial effects of the present application are:

[0112] Because the outside wall of the carrier rocket is coated with paint and has a certain arc, the traditional wall hanging device (such as a hook) relying on air pressure is insufficient in pressure, even if the volume is increased, only the contact area is increased, resulting in increased friction, without increasing the adsorption force, which cannot meet the requirements of anti-falling in the carrier rocket test operation, the present application comprehensively analyzes the dry environment outside the cabin of the carrier rocket, through the research on the structure and components of the outside cabin, combined with the special structure of the outside wall of the carrier rocket cabin, the fixed connecting piece is designed, which has larger pressure than the traditional wall hanging device, and can automatically adjust and prompt the pressure, can realize the reliable adsorption and regular replacement of the outside wall of the carrier rocket cabin, combined with the special structure of the load bag and the slide rail, the unmanned anti-falling measure outside the cabin can be realized, the utilization rate of the on-rocket operation personnel participating in the main operation post is greatly improved, the efficiency of the on-rocket test operation is improved to a certain extent, the operation risk of the on-rocket operation personnel is reduced, and the reliability of the rocket launch task is improved.

[0113] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A fall protection device for external testing operations of a launch vehicle, characterized in that, 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 arrestor for external testing operations 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. A fall arrestor for external testing operations 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; When using the fixed connector, the sealing plate is tightly attached to the bottom inner wall of the sealing gasket; below the target outside the launch vehicle cabin, after the bottom outer wall of the sealing gasket is tightly attached to the outer wall of the launch vehicle cabin, the rotating handle is turned to drive the threaded rod to rotate in the threaded seat, raising the sealing plate and separating it from the bottom inner wall of the sealing gasket. The volume of the cavity structure increases, the pressure difference with atmospheric pressure increases, and the sealing gasket is adsorbed and installed on the outer wall of the launch vehicle cabin. When replacing the fixed connector, rotate the handle in the opposite direction to drive the threaded rod to rotate in the opposite direction in the threaded seat. The sealing plate descends, the volume of the cavity structure decreases, the pressure difference with atmospheric pressure decreases, and the sealing gasket is removed from the outer wall of the launch vehicle cabin.

4. The fall arrestor for external testing operations 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. A fall arrestor for external testing operations 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, 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 to 90°.

6. The fall arrestor for external testing operations 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. A fall arrestor for external testing operations 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, 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 to 90°.

8. The fall arrestor for external testing operations of a launch vehicle according to claim 1, characterized in that, 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. A fall arrestor for external testing operations 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. When a pulling force is applied to the unlock button, the unlock spring is in a stretched state, the unlock slider moves upward, causing the connecting rod to rotate, the locking slider moves downward, causing the locking key to move downward, the locking spring is compressed, and the locking key disengages from the limiting groove, thus achieving the unlocked state.

10. A fall arrestor for external testing operations of a launch vehicle according to any one of claims 1-9, 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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