Pressure-sensitive rocket shell self-adaptive supporting device and supporting method thereof

Abstract

The pressure-sensitive rocket shell self-adaptive supporting device comprises an outer shell frame, the top of the outer shell frame is connected with a porous metal top plate, a plurality of upper sliding holes are formed in the porous metal top plate and distributed in a matrix mode, and supporting column unit bodies are arranged in the upper sliding holes in a sliding and penetrating mode; a base metal plate is fixedly connected to the position, close to the bottom, in the outer shell frame, a plurality of lower sliding holes are formed in the base metal plate and correspond to the upper sliding holes of the porous metal top plate, and each supporting column unit further penetrates through the corresponding lower sliding hole. Each supporting column unit body is connected with a limiting unit, and each limiting unit makes contact with the upper surface of the base metal plate. A plurality of second electromagnets are connected to the top face of the bottom of the outer shell frame. The invention further discloses a pressure-sensitive rocket shell self-adaptive supporting method. According to the pressure-sensitive type rocket shell self-adaptive supporting device and the supporting method thereof, the problem that an existing rocket shell supporting device cannot adapt to rocket shells of different sizes is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft structure support devices, and in particular to a pressure-sensitive rocket shell adaptive support device. The present invention also relates to a support method using the above-mentioned support device. Background Art

[0002] As a key structural component of a spacecraft, the rocket shell's stability and safety are particularly critical in every stage of manufacturing, transportation, and launch. Current rocket shell support devices are mostly customized in design, and in actual application, they have the following problems: Single size. Existing support devices can usually only adapt to rocket shells of a specific size. When faced with non-standardized or variable-sized rocket shells, their adaptability is obviously insufficient and they cannot meet diverse support needs. Low space utilization. In a production workshop or preparation site with limited space, it is necessary to stockpile multiple models of brackets to adapt to rocket shells of different sizes, occupying limited space resources. There are safety hazards. If the bracket and the rocket shell do not fit tightly and cannot provide stable support, there is a risk of overturning and sliding, posing a potential threat to personnel safety and equipment integrity.

[0003] The international patent "Rocket-Assisted Hydraulic Support Device," application number PCTCN2020126220, publication number WO2021088818A1, and publication date May 14, 2021, discloses a rocket-assisted hydraulic support device that can control the support force by adjusting the current of a proportional relief valve during the rocket erection process, while also being able to adapt to positioning deviations in the event of a launch termination. The Chinese patent "A Support Structure for Rocket Transportation and Launch and a Rocket Transportation Method," application number CN202410278818.3, publication number CN118220688A, and publication date June 21, 2024, proposes a support structure that solves the problem of excessive bearing surface pressure through the combination of multiple support members and adapters. The Chinese patent "Support device, support system and working method for launch vehicle", application number: CN202410370217.5, publication number: CN118289236A, publication date: 2024.07.05, discloses a support device for launch vehicle and its working method. The device adjusts the support force and support position through a hydraulic system, which can effectively reduce the ground load and improve the carrying capacity.

[0004] Although the above invention patents have optimized the structure of the rocket shell support device, the designed support device still cannot adapt to rocket shells of different sizes and it is difficult to provide a comprehensive support effect. Summary of the Invention

[0005] The purpose of the present invention is to provide a pressure-sensitive rocket shell adaptive support device, which solves the problem that the existing rocket shell support device cannot adapt to rocket shells of different sizes.

[0006] Another object of the present invention is to provide a method for supporting using the above-mentioned supporting device.

[0007] The first technical solution adopted by the present invention is: a pressure-sensitive rocket shell adaptive support device, including an outer shell frame, the top of the outer shell frame is connected to a porous metal top plate, a plurality of upper sliding holes are opened on the porous metal top plate, and the plurality of sliding holes are distributed in a matrix manner, and a support column unit body is slidably passed through each upper sliding hole; a base metal plate is fixedly connected to the inner part of the outer shell frame near the bottom position, and a plurality of lower sliding holes are opened on the base metal plate, and the lower sliding holes correspond to the upper sliding holes of the porous metal top plate, and each support column unit body also passes through the corresponding lower sliding hole; each support column unit body is respectively connected to a limiting unit, and each limiting unit is in contact with the upper surface of the base metal plate; the top surface of the bottom of the outer shell frame is connected to a plurality of second electromagnets corresponding to the support column unit bodies.

[0008] The first technical solution of the present invention is also characterized in that:

[0009] The support column unit body includes a metal cylinder, which is non-magnetic stainless steel. The top of the metal cylinder is connected to a pressure sensor, each pressure sensor is connected to a control unit through a signal line, and the bottom of the metal cylinder is connected to a magnet matching its diameter. The support column unit body is encapsulated with insulating rubber. The magnetism of the magnet is opposite to that of the second electromagnet, and the coil of each second electromagnet is connected to the control unit through a wire.

[0010] The limit unit includes a limit seat, which is a rectangular parallelepiped. A metal cylindrical hole is opened in the center of the limit seat. The metal cylinder passes through the metal cylindrical hole and is fixed to the limit seat. Several spring blind holes are evenly distributed on the limit seat with the metal cylindrical hole as the center. Each spring blind hole is connected to a limit spring, and the other end of each limit spring is in contact with the upper surface of the base metal plate.

[0011] The second technical solution adopted by the present invention is a pressure-sensitive rocket shell adaptive support method, which specifically includes the following steps:

[0012] S1: Place the rocket shell horizontally on two pressure-sensitive rocket shell adaptive support devices;

[0013] S2: The rocket shell contacts the corresponding pressure sensor and generates pressure thereon, and the corresponding pressure sensor transmits the corresponding pressure signal to the control unit;

[0014] S3: The control unit calculates and outputs a corresponding current to the corresponding second electromagnet according to the corresponding pressure signal received, and the support column unit body corresponding to the pressure sensor that is not in contact with the rocket shell rises to the highest position;

[0015] S4: The corresponding second electromagnet generates a uniform upward magnetic field, so that the support column unit body is separated from the corresponding second electromagnet, providing a vertical upward supporting force to support the rocket shell.

[0016] The second technical solution of the present invention is also characterized in that:

[0017] In S3, the current calculation formula is:

[0018]

[0019] Wherein, F is the electromagnetic force generated by the second electromagnet, μ0 is the vacuum magnetic permeability, N is the number of turns of the coil of the second electromagnet 5; I is the current, A is the cross-sectional area of ​​the iron core of the second electromagnet, and g is the air gap length.

[0020] The beneficial effects of the present invention are:

[0021] The use of the pressure-sensitive rocket shell adaptive support device and support method of the present invention produces the following effects: the electromagnet assembly inside the pressure-sensitive rocket shell adaptive support device of the present invention can adjust the current in real time according to the signal transmitted by the pressure sensor, accurately control the magnetic field interaction force, so as to adapt to the specific support requirements of the rocket shell, and achieve effective support for non-standardized or variable-sized rocket shells. The stability and safety of the rocket shell are significantly improved, and the risk of overturning and sliding of the rocket shell during storage and transportation is effectively reduced; the pressure-sensitive rocket shell adaptive support device and support method of the present invention are not only suitable for rocket shells, but can also adapt to aircraft parts of other shapes and sizes, providing a flexible and reliable solution for the support needs of the aerospace industry and other fields. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the main structure of the pressure-sensitive rocket shell adaptive support device of the present invention;

[0023] Figure 2 This is a schematic top view of the structure of the pressure-sensitive rocket shell adaptive support device of the present invention;

[0024] Figure 3 This is a flow chart of the pressure-sensitive rocket shell adaptive support method of the present invention;

[0025] Figure 4 This is a diagram showing the use effect of the pressure-sensitive rocket shell adaptive support device of the present invention.

[0026] In the figure: 1. Porous metal top plate; 2. Outer shell frame; 3. Metal cylinder; 4. Limit unit; 5. Second electromagnet; 6. Cooling system; 7. Pressure sensor; 8. Control unit; 9. Base metal plate. DETAILED DESCRIPTION

[0027] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0028] like Figure 1 As shown, the present invention provides a pressure-sensitive rocket shell adaptive support device, including an outer shell frame 2, the top of the outer shell frame 2 is connected to a porous metal top plate 1, the porous metal top plate 1 is provided with a plurality of upper sliding holes, the plurality of sliding holes are distributed in a matrix, and a support column unit body is slidably passed through each upper sliding hole; a base metal plate 9 is fixedly connected to the inner part of the outer shell frame 2 near the bottom, the base metal plate 9 is provided with a plurality of lower sliding holes, the lower sliding holes correspond to the upper sliding holes of the porous metal top plate 1, and each support column unit body also passes through the corresponding lower sliding hole; each support column unit body is respectively The limiting units 4 are connected, and each limiting unit 4 is in contact with the upper surface of the base metal plate 9; the top surface of the bottom of the outer shell frame 2 is connected with several second electromagnets 5 corresponding to the support column units; the porous metal top plate 1 and the outer shell frame 2 are made of non-magnetic stainless steel to ensure the overall structural strength of the support device, avoid interaction with the electromagnetic field generated internally, and isolate interference from the external environment; the surfaces of the porous metal top plate 1 and the outer shell frame 2 are sprayed with protective coating to prevent the metal substrate from corrosion and scratches; and a cooling system 6 is also included.

[0029] The cooling system 6 consists of a compressor, condenser, expansion valve, and evaporator. The compressor, driven by an electric motor, draws refrigerant vapor from the evaporator and increases its pressure and temperature through compression. The condenser, acting as a heat exchanger, absorbs heat from an ambient medium such as air or water, condensing the vapor into a high-pressure liquid. This high-pressure liquid then passes through the expansion valve to reduce its pressure and temperature, becoming a low-temperature, low-pressure liquid before entering the evaporator. Within the evaporator, the refrigerant evaporates and absorbs heat, achieving a cooling process.

[0030] The support column unit body includes a metal cylinder 3, which is non-magnetic stainless steel. The top of the metal cylinder 3 is connected to a pressure sensor 7, and each pressure sensor 7 is connected to a control unit 8 through a signal line. The bottom of the metal cylinder 3 is connected to a magnet matching its diameter. The support column unit body is encapsulated with insulating rubber to prevent the rocket shell from making rigid contact with the metal bracket, and at the same time reduce the friction between the metal cylinder and other components during vertical movement; the magnet has opposite magnetic properties to the second electromagnet 5, and the coil of each second electromagnet 5 is respectively connected to the control unit 8 through a wire.

[0031] like Figure 1 and Figure 2 As shown, the limit unit 4 includes a limit seat, which is a rectangular parallelepiped. The material, aperture size and distribution of the limit seat are the same as those of the porous metal top plate 1. A metal cylindrical hole is opened in the center of the limit seat. The metal cylinder 3 passes through the metal cylindrical hole and is fixed to the limit seat. A number of spring blind holes are evenly distributed along the metal cylindrical hole as the center of the limit seat. A limit spring is connected in each spring blind hole. The other end of each limit spring contacts the upper surface of the base metal plate 9, which is used to limit the axial displacement of the support column unit under electromagnetic induction drive and provide necessary buffering.

[0032] The pressure-sensitive rocket shell adaptive support device provided by the present invention has the following working principle: when the rocket shell is placed horizontally on the support device, the pressure sensor 7 at the top of the support column unit body converts the pressure it feels into an electrical signal and transmits it to the control unit 8. Based on the received signal, the control unit 8 matches and outputs the corresponding current signal to the second electromagnet 5, thereby generating a magnetic field with an opposite magnetic pole to the electromagnet at the lower end of the metal cylinder. This action separates the support column unit body from the second electromagnet 5 and provides a vertical upward supporting force. Each independent support column unit body moves adaptively according to the force conditions to dynamically adjust the supporting force to ensure that the rocket shell is stably supported.

[0033] During operation, due to the heavy weight of the rocket shell or the prolonged operation of the device, the electromagnet may overheat, affecting the device's performance and efficiency. To address this, the cooling system, through the coordinated operation of a compressor, condenser, expansion valve, and evaporator, effectively reduces the internal temperature of the device and improves its operational stability. The specific operating process involves four stages: compression, heat release, throttling, and heat absorption, forming a continuous refrigeration cycle to ensure optimal performance under all operating conditions.

[0034] like Figure 3 and Figure 4 As shown, the present invention provides a pressure-sensitive rocket shell adaptive support method, which specifically includes the following steps:

[0035] S1: Place the rocket shell horizontally on two pressure-sensitive rocket shell adaptive support devices;

[0036] S2: The rocket shell contacts the corresponding pressure sensor 7 and generates pressure thereon, and the corresponding pressure sensor 7 transmits the corresponding pressure signal to the control unit 8;

[0037] S3: The control unit 8 calculates and outputs the corresponding current to the corresponding second electromagnet 5 according to the corresponding pressure signal received, and the support column unit body corresponding to the pressure sensor 7 that is not in contact with the rocket shell rises to the highest position; the current calculation formula is:

[0038]

[0039] Wherein, F is the electromagnetic force generated by the second electromagnet 5, μ0 is the vacuum magnetic permeability, N is the number of turns of the coil of the second electromagnet 5; I is the current, A is the cross-sectional area of ​​the iron core of the second electromagnet 5, and g is the air gap length.

[0040] S4: The corresponding second electromagnet 5 generates a uniform upward magnetic field, so that the support column unit body is separated from the corresponding second electromagnet 5, providing a vertical upward supporting force to support the rocket shell.

[0041] Example 1

[0042] like Figure 1 As shown, the pressure-sensitive rocket shell adaptive support device proposed in this embodiment includes an outer shell frame 2, and the top of the outer shell frame 2 is connected to a porous metal top plate 1, and the porous metal top plate 1 is provided with a plurality of upper sliding holes, and the plurality of sliding holes are distributed in a matrix manner, and a support column unit body is slidably passed through each upper sliding hole; a base metal plate 9 is fixedly connected to the inner part of the outer shell frame 2 near the bottom position, and a plurality of lower sliding holes are provided on the base metal plate 9, and the lower sliding holes correspond to the upper sliding holes of the porous metal top plate 1, and each support column unit body also passes through the corresponding lower sliding hole; each support column unit body is respectively connected to a limiting unit 4, and each limiting unit 4 is in contact with the upper surface of the base metal plate 9; the top surface of the bottom of the outer shell frame 2 is connected with a plurality of second electromagnets 5 corresponding to the support column unit bodies.

[0043] Example 2

[0044] like Figure 1 and 2As shown, the pressure-sensitive rocket shell adaptive support device proposed in this embodiment includes an outer shell frame 2, and the top of the outer shell frame 2 is connected to a porous metal top plate 1, and the porous metal top plate 1 is provided with a plurality of upper sliding holes, and the plurality of sliding holes are distributed in a matrix manner, and a support column unit body is slidably passed through each upper sliding hole; a base metal plate 9 is fixedly connected to the inner part of the outer shell frame 2 near the bottom position, and a plurality of lower sliding holes are provided on the base metal plate 9, and the lower sliding holes correspond to the upper sliding holes of the porous metal top plate 1, and each support column unit body also passes through the corresponding lower sliding hole; each support column unit body is respectively connected to a limiting unit 4, and each limiting unit 4 is in contact with the upper surface of the base metal plate 9; the top surface of the bottom of the outer shell frame 2 is connected with a plurality of second electromagnets 5 corresponding to the support column unit bodies. The support column unit body includes a metal cylinder 3, which is made of non-magnetic stainless steel. The top of the metal cylinder 3 is connected to a pressure sensor 7. Each pressure sensor 7 is connected to a control unit 8 via a signal line. The bottom of the metal cylinder 3 is connected to a magnet that matches its diameter. The support column unit body is encapsulated with insulating rubber. The magnet has opposite magnetic properties to the second electromagnet 5. The coil of each second electromagnet 5 is connected to the control unit 8 via a wire. The limit unit 4 includes a limit seat. The limit seat is a rectangular parallelepiped. The center of the limit seat is provided with a metal cylindrical hole. The metal cylinder 3 passes through the metal cylindrical hole and is fixed to the limit seat. The limit seat has a number of spring blind holes evenly distributed along the metal cylindrical hole as the center. Each spring blind hole is connected to a limit spring. The other end of each limit spring is in contact with the upper surface of the base metal plate 9.

[0045] Example 3

[0046] like Figure 3 and 4 As shown, the present invention provides a pressure-sensitive rocket shell adaptive support method, which specifically includes the following steps:

[0047] S1: Place the rocket shell horizontally on two pressure-sensitive rocket shell adaptive support devices;

[0048] S2: The rocket shell contacts the corresponding pressure sensor 7 and generates pressure thereon, and the corresponding pressure sensor 7 transmits the corresponding pressure signal to the control unit 8;

[0049] S3: The control unit 8 calculates and outputs a corresponding current to the corresponding second electromagnet 5 according to the corresponding pressure signal received, and the support column unit body corresponding to the pressure sensor 7 that is not in contact with the rocket shell rises to the highest position;

[0050] S4: The corresponding second electromagnet 5 generates a uniform upward magnetic field, so that the support column unit body is separated from the corresponding second electromagnet 5, providing a vertical upward supporting force to support the rocket shell.

[0051] Example 4

[0052] like Figure 3 and 4 As shown, the present invention provides a pressure-sensitive rocket shell adaptive support method, which specifically includes the following steps:

[0053] S1: Place the rocket shell horizontally on two pressure-sensitive rocket shell adaptive support devices;

[0054] S2: The rocket shell contacts the corresponding pressure sensor 7 and generates pressure thereon, and the corresponding pressure sensor 7 transmits the corresponding pressure signal to the control unit 8;

[0055] S3: The control unit 8 calculates and outputs the corresponding current to the corresponding second electromagnet 5 according to the corresponding pressure signal received, and the support column unit body corresponding to the pressure sensor 7 that is not in contact with the rocket shell rises to the highest position; the current calculation formula is:

[0056]

[0057] Wherein, F is the electromagnetic force generated by the second electromagnet 5, μ0 is the vacuum magnetic permeability, N is the number of turns of the coil of the second electromagnet 5; I is the current, A is the cross-sectional area of ​​the iron core of the second electromagnet 5, and g is the air gap length.

[0058] S4: The corresponding second electromagnet 5 generates a uniform upward magnetic field, so that the support column unit body is separated from the corresponding second electromagnet 5, providing a vertical upward supporting force to support the rocket shell.

Claims

1. A pressure-sensitive rocket shell adaptive support device, characterized in that: The invention comprises an outer shell frame (2), the top of which is connected to a porous metal top plate (1), a plurality of upper sliding holes are provided on the porous metal top plate (1), the plurality of sliding holes are distributed in a matrix, and a support column unit body is slidably penetrated in each of the upper sliding holes; a base metal plate (9) is fixedly connected to the inner part of the outer shell frame (2) near the bottom, the base metal plate (9) is provided with a plurality of lower sliding holes, the lower sliding holes correspond to the upper sliding holes of the porous metal top plate (1), and each of the support column unit bodies also passes through the corresponding lower sliding holes; each of the support column unit bodies is respectively connected to a limiting unit (4), and each of the limiting units (4) is in contact with the upper surface of the base metal plate (9); and a plurality of second electromagnets (5) corresponding to the support column unit bodies are connected to the top surface of the bottom of the outer shell frame (2).

2. The pressure-sensitive rocket shell adaptive support device according to claim 1 is characterized in that: The support column unit body comprises a metal cylinder (3), the metal cylinder (3) is made of non-magnetic stainless steel, the top of the metal cylinder (3) is connected to a pressure sensor (7), each of the pressure sensors (7) is connected to a control unit (8) via a signal line, the bottom of the metal cylinder (3) is connected to a magnet matching its diameter, the support column unit body is encapsulated with insulating rubber, the magnet has opposite magnetic properties to the second electromagnet (5), and each coil of the second electromagnet (5) is connected to the control unit (8) via a wire.

3. The pressure-sensitive rocket shell adaptive support device according to claim 2 is characterized in that: The limit unit (4) comprises a limit seat, the limit seat is in the shape of a rectangular parallelepiped, a metal cylindrical hole is opened at the center of the limit seat, the metal cylinder (3) passes through the metal cylindrical hole and is fixedly connected to the limit seat, and a plurality of spring blind holes are evenly distributed on the limit seat with the metal cylindrical hole as the center, each of the spring blind holes is connected to a limit spring, and the other end of each limit spring is in contact with the upper surface of the base metal plate (9).

4. A pressure-sensitive rocket shell adaptive support method, characterized in that: Using the pressure-sensitive rocket shell adaptive support device as claimed in claim 3 specifically comprises the following steps: S1: Place the rocket shell horizontally on two pressure-sensitive rocket shell adaptive support devices; S2: The rocket shell contacts the corresponding pressure sensor (7) and generates pressure thereon, and the corresponding pressure sensor (7) transmits the corresponding pressure signal to the control unit (8); S3: The control unit (8) calculates and outputs a corresponding current to the corresponding second electromagnet (5) according to the corresponding pressure signal received, and the support column unit body corresponding to the pressure sensor (7) not in contact with the rocket shell rises to the highest position; S4: The corresponding second electromagnet (5) generates a uniform upward magnetic field, so that the support column unit body is separated from the corresponding second electromagnet (5), providing a vertical upward supporting force to support the rocket shell.

5. The pressure-sensitive rocket shell adaptive support method according to claim 4 is characterized in that: In S3, the current calculation formula is: Wherein, F is the electromagnetic force generated by the second electromagnet (5), μ0 is the vacuum magnetic permeability, N is the number of turns of the coil of the second electromagnet (5); I is the current, A is the cross-sectional area of ​​the iron core of the second electromagnet (5), and g is the air gap length.

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