Measuring system for external inspection of spaceflight pressure storage tank

Abstract

The utility model provides a measuring system for external inspection of a spaceflight pressure storage tank, which comprises a rotary supporting platform and an omnibearing measuring mechanism positioned on one side of the rotary supporting platform, and the rotary supporting platform is provided with a first rotary driving device and a tank body bracket mounted on the first rotary driving device. The tank body bracket is provided with an adjustable clamp for fixing the spaceflight pressure storage tank; the omni-directional measurement mechanism comprises an X-axis movement mechanism, a Y-axis movement mechanism and a two-axis turnover mechanism, the Y-axis movement mechanism is installed on the X-axis movement mechanism in a sliding mode in the X-axis direction, and the two-axis turnover mechanism is installed on the Y-axis movement mechanism in a sliding mode in the Y-axis direction; and the two-shaft turnover mechanism is used for driving the tank body measuring equipment to do up-down pitching swing and do circumferential rotation along the axis. Through omnibearing and multi-angle automatic pose control, comprehensive detection of the spaceflight pressure storage tank is realized, and comprehensiveness and reliability of detection are ensured.

Description

Technical Field

[0001] The utility model relates to aerospace pressure storage tank testing, in particular to a measuring system for external inspection of aerospace pressure storage tanks. Background Art

[0002] Space pressure tanks are essential components of spacecraft, widely used to store critical gases and liquids such as propellants, oxidizers, helium, and nitrogen. These tanks play a vital role in the spacecraft's propulsion system, attitude control system, and life support system. In the harsh space environment, pressure tanks must not only withstand drastic temperature fluctuations and mechanical stress, but also maintain high pressure in a vacuum environment for extended periods to ensure the safe operation of the spacecraft. Any slight deformation or structural defect could lead to propulsion system failure, loss of attitude control, or even endanger the lives of astronauts. Therefore, the structural integrity and sealing of space pressure tanks are crucial to their safety.

[0003] During space missions, external inspections of pressure tanks cover several key parameters, including roundness, wall thickness, weld quality, flatness, and deformation. These inspections are crucial because the geometry and structural condition of pressure tanks directly impact their performance and safety. Roundness testing ensures that the tanks do not experience uneven stress distribution under high pressure, thereby preventing damage. Wall thickness uniformity testing ensures that the tanks can withstand pressure fluctuations in extreme environments. Any area of ​​uneven wall thickness can become a weak point, increasing the risk of failure. Weld quality is the most vulnerable link in the tank structure. Cracks, pores, or other discontinuities can lead to leakage or rupture during operation. Surface flatness testing helps detect surface irregularities, which can cause localized stress concentrations and lead to structural failure under high pressure or vacuum conditions. Deformation testing ensures that the tanks have not undergone physical deformation during manufacturing, transportation, and use, thus maintaining their structural integrity. Through comprehensive external inspections, the reliability and safety of space pressure tanks under extreme conditions can be ensured, preventing any impact on the normal operation of the spacecraft.

[0004] Currently, external inspection of storage tanks relies primarily on manual labor. Workers use measuring instruments such as laser rangefinders and ultrasonic thickness gauges to measure parameters such as the tank's diameter, height, roundness, wall thickness, and welds point by point. However, this method has significant limitations: the accuracy of manual measurement depends on the operator's experience and skill, which is prone to measurement errors. Furthermore, manual measurement is time-consuming, point-by-point, and inefficient, making it difficult to achieve comprehensive and accurate coverage. Furthermore, in extreme environments such as high temperature, high pressure, or vacuum, manual inspection is both feasible and unsafe, as operators cannot directly access the tanks for inspection. This not only increases the difficulty of the operation but also poses a risk to personnel safety. Therefore, the use of automated inspection equipment is particularly necessary. The introduction of automated inspection equipment allows for high-precision, comprehensive external inspections in harsh environments, ensuring data accuracy while improving inspection efficiency and safety.

[0005] The existing technology has the following major shortcomings in the external inspection of pressure storage tanks:

[0006] 1. Insufficient detection accuracy: Manual measurement relies on the operator's experience and skills. The measurement accuracy is easily affected by human factors, making it difficult to achieve all-round accurate measurement.

[0007] 2. Inefficiency: Manual point-by-point measurement is time-consuming and inefficient. The adjustment and operation of traditional measuring equipment are complicated, which further reduces the detection speed and cannot meet the detection needs of the modern aerospace industry.

[0008] 3. Complex operation and poor flexibility: Existing testing technologies are cumbersome to operate, and measuring equipment is difficult to flexibly adjust to accommodate the varying sizes and shapes of pressure storage tanks. This is especially true when faced with diverse testing scenarios, as existing equipment lacks sufficient flexibility to efficiently address diverse testing requirements.

[0009] Poor environmental adaptability: Manual measurement is less adaptable to specialized environments, particularly extreme temperatures, high pressures, or vacuums, which significantly restricts manual operation. These conditions not only endanger operator safety but also affect the accuracy and efficiency of inspections. In some cases, operators are unable to enter extreme environments for measurement or must utilize expensive and complex protective equipment, further reducing the feasibility and safety of inspections.

[0010] Existing external inspection methods for aerospace pressure tanks suffer from manual measurement errors, low efficiency, and operational difficulties in extreme environments, making them unable to meet the inspection needs of the modern aerospace industry. Therefore, a solution that can achieve automated, comprehensive, and safe inspection is urgently needed to address the shortcomings of existing technologies and improve inspection reliability and efficiency. Utility Model Content

[0011] The utility model provides an all-round multi-angle automatic posture control measurement system for the external inspection of aerospace pressure storage tanks. The measurement system detects the aerospace pressure storage tanks through a tank body measurement device. The measurement system includes a rotary support platform and an all-round measurement mechanism located on one side of the rotary support platform.

[0012] The slewing support platform is provided with a first rotary drive device and a tank bracket mounted on the first rotary drive device, and the tank bracket is provided with an adjustable clamp for fixing the aerospace pressure storage tank;

[0013] The omnidirectional measuring mechanism includes an X-axis motion mechanism, a Y-axis motion mechanism, and a two-axis flipping mechanism. The Y-axis motion mechanism is mounted on the X-axis motion mechanism while sliding along the X-axis direction. The two-axis flipping mechanism is mounted on the Y-axis motion mechanism while sliding along the Y-axis direction. The two-axis flipping mechanism is used to drive the tank measuring equipment to perform up and down pitching and circumferential rotation.

[0014] Furthermore, the measuring system includes an outer box installed on the ground, and the tank bracket and the omnidirectional measuring mechanism are all installed in the outer box.

[0015] Furthermore, the first rotary drive device is arranged in a trench opened on the ground. The first rotary drive device is provided with a first drive motor, a transmission system and an output shaft. The first drive motor drives the output shaft to rotate through the transmission system, and the output shaft is fixedly connected to the tank bracket.

[0016] Furthermore, a transmission system is mounted on a base bracket, the transmission system includes a coupling, a transmission shaft, a first bevel gear, a second bevel gear, a first drive motor is fixedly mounted on the base bracket, a first bearing seat and a second bearing seat are mounted on the base bracket, and the transmission shaft and the output shaft are rotatably mounted on the first bearing seat and the second bearing seat respectively;

[0017] The first drive motor is connected to one end of the transmission shaft through a coupling. The other end of the transmission shaft is fixed with a first bevel gear. The first bevel gear is meshed with a second bevel gear. The second bevel gear is fixedly mounted on the output shaft.

[0018] Furthermore, the tank bracket includes a turntable base, which is connected to the first rotation drive device. An adjustable clamp is fixedly mounted on the upper surface of the turntable base. The adjustable clamp includes at least three sets of adjustment racks that are circumferentially distributed and centrally symmetrical. The aerospace pressure storage tank is placed in a funnel-shaped opening formed between the adjustment racks.

[0019] Each adjustment frame is provided with an oblique support arm, an insertion rod, a sleeve and a latch. The bottom of the oblique support arm is rotatably connected to the turntable base, the top of the oblique support arm is rotatably connected to the insertion rod, the insertion rod is inserted into the sleeve, and the bottom of the sleeve is rotatably connected to the turntable base. The sleeve and the insertion rod are provided with a row of latch holes with the same spacing. The latch is inserted into the overlapping latch holes of the sleeve and the insertion rod to lock the adjustment frame.

[0020] Furthermore, the X-axis motion mechanism includes an X-axis track, an X-axis driving device and a first slider, and the X-axis track is fixedly mounted with an X-axis rack.

[0021] The X-axis drive device and the Y-axis motion mechanism are both fixedly mounted on the first slider. The X-axis drive device drives the first slider to slide along the X-axis track. The X-axis drive device includes a second drive motor and a second drive gear mounted on the output shaft of the second drive motor. The second drive gear engages with the X-axis rack.

[0022] Furthermore, the Y-axis motion mechanism includes a Y-axis track, a Y-axis driving device and a second slider;

[0023] The Y-axis track is fixed with a Y-axis rack.

[0024] The Y-axis driving device and the two-axis flipping mechanism are installed on the second slider. The Y-axis driving device drives the second slider to slide on the Y-axis track. The Y-axis driving device includes a third driving motor and a third driving gear installed on the output shaft of the third driving motor. The third driving gear is engaged with the Y-axis rack.

[0025] Furthermore, the Y-axis motion mechanism is driven to slide along the X-axis and / or the two-axis flip mechanism is driven to slide along the Y-axis by a synchronous belt transmission mechanism or a ball screw transmission mechanism.

[0026] Furthermore, the two-axis flip mechanism includes a circumferential rotation mechanism and a pitch swing mechanism.

[0027] The circumferential rotation mechanism includes a second rotation drive device and a U-shaped rotating frame. The second rotation drive device includes a fourth drive motor, a worm gear, and a worm. The worm gear is mounted on the output shaft of the fourth drive motor. The worm gear is rotationally connected to the worm gear, and the worm gear is fixedly connected to the rotating frame.

[0028] The pitching and swinging mechanism includes a fifth driving motor. The tank body measuring device is mounted on a rotating frame for up and down rotation. The fifth driving motor drives the tank body measuring device to do pitching and swinging on the rotating frame.

[0029] A method for external inspection of aerospace pressure storage tanks based on the above-mentioned measurement system comprises the following steps:

[0030] Adjust the adjustable clamp and place the aerospace pressure storage tank on the adjustable clamp;

[0031] The first rotary drive device drives the tank bracket to rotate, and

[0032] The tank measuring equipment is driven to move by the X-axis motion mechanism, Y-axis motion mechanism, and two-axis flipping mechanism to perform all-round and multi-angle inspections on aerospace pressure storage tanks.

[0033] The advantages of the present invention are:

[0034] 1. Improved detection flexibility and adaptability, able to quickly adjust to accommodate pressure storage tanks of different sizes and shapes, meeting diverse detection scenario requirements.

[0035] 2. Through automated operation, the detection efficiency is significantly improved, the error of manual measurement is reduced, and the accuracy of the test results is ensured.

[0036] 3. Improved environmental adaptability enables safe and efficient testing even in special environments such as extreme temperature, high pressure or vacuum, ensuring the safety of operators.

[0037] 4. Reduce the dependence on expensive and complex protective equipment, improve the feasibility and safety of detection work, and reduce costs.

[0038] 5. Through all-round and multi-angle automatic posture control, comprehensive inspection of aerospace pressure storage tanks is achieved, ensuring the comprehensiveness and reliability of the inspection. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0040] Figure 1 This is an overall schematic diagram of the omnidirectional and multi-angle automatic posture control measurement system with an outer box of the utility model;

[0041] Figure 2 for Figure 1 Schematic diagram of the structure after the outer box is hidden;

[0042] Figure 3 This is a three-dimensional structural diagram of the slewing support platform;

[0043] Figure 4 This is a three-dimensional structural diagram of the slewing support platform from another perspective;

[0044] Figure 5 This is the main view of the slewing support platform;

[0045] Figure 6 This is a structural diagram of one set of adjustment frames of the adjustable fixture;

[0046] Figure 7 Schematic diagram of the structure of the adjustable fixture in different states;

[0047] Figure 8 This is the structural diagram of the omnidirectional measurement mechanism;

[0048] Figure 9 This is the main view of the omnidirectional measuring mechanism;

[0049] Figure 10 It is the structural diagram of the X-axis motion mechanism;

[0050] Figure 11 It is the structural diagram of the Y-axis motion mechanism;

[0051] Figure 12 This is the structural diagram of the two-axis flip mechanism. DETAILED DESCRIPTION

[0052] In the following description, numerous specific details are provided to provide a more thorough understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention can be practiced without one or more of these details. In other instances, certain technical features known in the art are not described to avoid confusion with the present invention.

[0053] In order to fully understand the present invention, detailed steps and detailed structures will be provided in the following description to illustrate the technical solution of the present invention. The preferred embodiments of the present invention are described in detail below. However, in addition to these detailed descriptions, the present invention may also have other implementation methods.

[0054] Reference Figure 1-2 As shown, the present invention provides an omnidirectional, multi-angle, automatic posture control and measurement system for the external inspection of aerospace pressure storage tanks. The measurement system inspects aerospace pressure storage tanks 4 using a tank measuring device 3. The measurement system comprises a slewing support platform 1 and an omnidirectional measurement mechanism 2 located on one side of the slewing support platform 1. The tank bracket 12 and the omnidirectional measurement mechanism 2 are both mounted within an outer box 5 on the ground. The outer box 5 provides partial light shielding and protection, improving the inspection accuracy of the omnidirectional measurement mechanism 2.

[0055] Slewing support platform 1

[0056] The rotary support platform 1 is provided with a first rotary drive device 11 and a tank bracket 12 mounted on the first rotary drive device 11 . The tank bracket 12 is provided with an adjustable clamp 121 for fixing the aerospace pressure storage tank 4 .

[0057] like Figure 2-5As shown, the first rotary drive device 11 is arranged in a trench 6 opened on the ground. The first rotary drive device 11 is provided with a first drive motor 111, a transmission system 112 and an output shaft 113. The first drive motor 111 drives the output shaft 113 to rotate through the transmission system 112, and the output shaft 113 is fixedly connected to the tank bracket 12.

[0058] The transmission system 112 is mounted on a base bracket 1121, which is fixed in the trench 6. The transmission system 112 includes a coupling 1122, a transmission shaft 1123, a first bevel gear 1124, and a second bevel gear 1125. The first drive motor 111 is fixedly mounted on the base bracket 1121, and a first bearing seat 1126 and a second bearing seat 1127 are mounted on the base bracket 1121. The transmission shaft 1123 and the output shaft 113 are rotatably mounted on the first bearing seat 1126 and the second bearing seat 1127 respectively; the first drive motor 111 is connected to one end of the transmission shaft 1123 through the coupling 1122, and the other end of the transmission shaft 1123 is fixed with a first bevel gear 1124, which meshes with the second bevel gear 1125, and the second bevel gear 1125 is fixedly mounted on the output shaft 113. The power of the first drive motor 111 is transmitted to the transmission shaft 1123 through the coupling 1122 to make it rotate, and by meshing the first bevel gear 1124 and the second bevel gear 1125, the output shaft 113 and the turntable base 122 are rotated horizontally, and finally the aerospace pressure storage tank 4 on the turntable base 122 is rotated 360° horizontally, so that the tank body measuring equipment 3 of the slewing support platform 1 can perform 360° horizontal detection on the aerospace pressure storage tank 4.

[0059] The tank bracket 12 includes a turntable base 122, which is fixedly connected to the output shaft 113. An adjustable clamp 121 is fixedly installed on the upper surface of the turntable base 122. The adjustable clamp 121 consists of three sets of adjustment frames 1211 distributed circumferentially and symmetrically. The aerospace pressure storage tank 4 is placed in the funnel-shaped opening formed between the adjustment frames 1211 (such as Figure 7 shown).

[0060] Figure 6The diagram shows the structure of a single adjustment frame 1211. Each adjustment frame 1211 is equipped with an oblique support arm 1212, a rod 1213, a sleeve 1214, and a latch. The bottom of the oblique support arm 1212 is rotatably connected to the turntable base 122, and the top of the oblique support arm 1212 is rotatably connected to the rod 1213. The rod 1213 is inserted into the sleeve 1214, and the bottom of the sleeve 1214 is rotatably connected to the turntable base 122. The sleeve 1214 and the rod 1213 are each provided with a row of equally spaced latch holes 1215. The latch is inserted into the overlapping latch holes 1215 of the sleeve 1214 and the rod 1213 to lock the adjustment frame 1211. Two hinged seats 1216 are fixedly mounted on the turntable base 122, which are rotatably connected to the sleeve 1214 and the bottom of the oblique support arm 1212, respectively. By inserting the pins into different pin holes 1215, the angle of the oblique support arm 1212 can be adjusted, thereby adjusting the size of the funnel-shaped opening, such as Figure 7 As shown, it can adapt to aerospace pressure storage tanks 4 of different sizes, and at the same time, the height and elevation angle of the aerospace pressure storage tank 4 can be adjusted, with a higher degree of adjustment freedom.

[0061] Omnidirectional measuring mechanism 2

[0062] The omnidirectional measuring mechanism 2 includes an X-axis motion mechanism 21, a Y-axis motion mechanism 22, and a two-axis flipping mechanism 23. The Y-axis motion mechanism 22 is slidably mounted on the X-axis motion mechanism 21 along the X-axis direction, and the two-axis flipping mechanism 23 is slidably mounted on the Y-axis motion mechanism 22 along the Y-axis direction. The two-axis flipping mechanism 23 is used to drive the tank measuring device 3 to perform up and down pitch swings and circumferential rotation along the axis.

[0063] 1) X-axis motion mechanism 21

[0064] like Figure 8-10 As shown, the X-axis motion mechanism 21 is fixedly mounted on a ground bracket 214. The X-axis motion mechanism 21 includes two X-axis rails 211, an X-axis drive device 212 and a first slider 213. The X-axis rail 211 is fixedly mounted with an X-axis rack 2111. The X-axis drive device 212 and the Y-axis motion mechanism 22 are both fixedly mounted on the first slider 213, and the X-axis drive device 212 drives the first slider 213 to slide along the X-axis on the X-axis rail 211. The X-axis drive device 212 includes a second drive motor and a second drive gear mounted on the output shaft of the second drive motor, and the second drive gear engages with the X-axis rack 2111. Through the X-axis motion mechanism 21, the tank body measuring device 3 can be driven to approach or move away from the aerospace pressure storage tank 4 in the X direction to adjust and change the distance between the tank body measuring device 3 and the aerospace pressure storage tank 4 to achieve near-field detection or far-field detection.

[0065] 2) Y-axis motion mechanism 22

[0066] like Figure 8-9as well as Figure 11 As shown, the Y-axis motion mechanism 22 includes two Y-axis rails 221, a Y-axis drive device 222, and a second slider 223. The Y-axis rail 221 is fixedly mounted with a Y-axis rack 2211. The Y-axis drive device 222 and the two-axis flip mechanism 23 are mounted on the second slider 223. The Y-axis drive device 222 drives the second slider 223 to slide along the Y-axis on the Y-axis rail 221. The Y-axis drive device 222 includes a third drive motor and a third drive gear mounted on the output shaft of the third drive motor. The third drive gear engages with the Y-axis rack 2211. The Y-axis motion mechanism 22 can drive the tank body measuring device 3 to move up and down in the Y direction to adjust the height of the tank body measuring device 3 and perform inspections on different heights of the aerospace pressure storage tank 4.

[0067] In some other embodiments, the Y-axis motion mechanism 22 can be driven to slide along the X-axis and / or the two-axis flipping mechanism 23 can be driven to slide along the Y-axis by a synchronous belt drive mechanism or a ball screw drive mechanism. The synchronous belt drive mechanism or the ball screw drive mechanism is common knowledge to those skilled in the art and will not be described in detail here.

[0068] 3) Two-axis flip mechanism 23

[0069] like Figure 12 As shown, the two-axis flip mechanism 23 includes a circumferential rotation mechanism 231 and a pitching and swinging mechanism 232. The circumferential rotation mechanism 231 includes a second rotation drive device 2311 and a U-shaped turret 2312. The second rotation drive device 2311 includes a fourth drive motor 2313, a worm gear 2314, and a worm 2315. The worm 2315 is mounted on the output shaft of the fourth drive motor 2313 and is rotationally connected to the worm gear 2314. The worm gear 2314 is rotatably mounted on the second slider 223 and fixedly connected to the turret 2312. The rotation of the fourth drive motor 2313 drives the turret 2312 to rotate 360 ​​degrees.

[0070] The pitch and swing mechanism 232 includes a fifth drive motor 2321. The tank measurement device 3 is mounted on a turret 2312 for vertical rotation. The fifth drive motor 2321 drives the tank measurement device 3 to pitch and swing on the turret 2312. The two-axis tilt mechanism 23 can drive the tank measurement device 3 to pitch and rotate 360° around the axis of the worm gear 2314, further enhancing the tank measurement device 3's freedom of movement within the spatial coordinate system, enabling comprehensive inspection of aerospace pressure storage tanks 4.

[0071] Electronic control system

[0072] The electronic control system is centrally installed in an electrical control box on one side of the platform. Cables connect the servo drive mechanisms and controllers of the slewing support platform 1 and the omnidirectional measurement mechanism 2, enabling unified and coordinated control of each motion mechanism. The electronic control system is equipped with an operation interface that allows the operator to set the motion trajectory, speed, and angle of each axis.

[0073] The method for external inspection of aerospace pressure storage tanks using the utility model comprises the following steps:

[0074] 1) Fixing the aerospace pressure storage tank 4: Adjust the adjustable clamp 121 so that its opening is adapted to the size of the aerospace pressure storage tank 4 to be tested. Then, lift the aerospace pressure storage tank 4 and place it on the adjustable clamp 121. Perform a trial run of the slewing support platform 1. The first rotary drive device 11 rotates, causing the tank body bracket 12 to drive the aerospace pressure storage tank 4 to rotate together. Observe whether the aerospace pressure storage tank 4 is properly installed.

[0075] 2) System Testing: The first rotary drive device 11 drives the tank bracket 12 to perform 360° horizontal rotation, and drives the tank measuring device 3 to perform X-axis motion, Y-axis motion, up and down pitch, and 360° rotation around the axis of the worm gear 2314 through the X-axis motion mechanism 21, Y-axis motion mechanism 22, and two-axis flip mechanism 23, to perform all-round and multi-angle inspection of the aerospace pressure storage tank.

[0076] The advantages of the present invention are:

[0077] 1) High-precision detection: The utility model can realize multi-angle and all-round high-precision detection of aerospace pressure storage tanks through an automated detection platform, avoiding errors caused by manual operation and ensuring the accuracy of measurement results.

[0078] 2) Improved efficiency: Compared to traditional manual point-by-point measurement methods, this utility model significantly increases the speed of inspection through automated equipment. The automated inspection platform can quickly cover all key parts of the tank, reducing inspection time.

[0079] 3) Strong environmental adaptability: The detection platform of this utility model can operate normally in extreme environments (such as high temperature, high pressure, and vacuum), solving the problem of manual inspection being impossible in these environments. This not only improves the flexibility of external tank inspection, but also ensures the safety of inspection operations.

[0080] 4) Efficient Automated Operation: Unlike existing technologies that rely on manual measurement, this utility model uses an automated testing platform, which can greatly improve testing efficiency. Without manual intervention, the system can quickly complete the external inspection of pressure storage tanks, significantly reducing inspection time.

[0081] 5) Flexible Adaptability: This new platform offers a high degree of flexibility, automatically adjusting the measurement path and detection method to suit the size and shape of different pressure storage tanks. Compared to existing technologies that require frequent repositioning of measurement tools, this platform can easily adapt to the various pressure storage tank inspection requirements, greatly improving operational convenience.

[0082] The above describes the preferred embodiments of the present invention. It should be understood that the present invention is not limited to the above-mentioned specific embodiments, and the devices and structures that are not described in detail should be understood to be implemented in a common manner in the art; any technician familiar with the art can use the above-mentioned disclosed methods and technical contents to make many possible changes and modifications to the technical solutions of the present invention without departing from the scope of the technical solution of the present invention, or modify them into equivalent embodiments with equivalent changes, which does not affect the essential content of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention that do not depart from the content of the technical solution of the present invention are still within the scope of protection of the technical solution of the present invention.

Claims

1. A measurement system for external inspection of aerospace pressure storage tanks, wherein the measurement system detects the aerospace pressure storage tank (4) through a tank body measurement device (3), characterized in that: The measuring system comprises a rotary support platform (1) and an omnidirectional measuring mechanism (2) located on one side of the rotary support platform (1). The rotary support platform (1) is provided with a first rotary drive device (11) and a tank bracket (12) mounted on the first rotary drive device (11), and the tank bracket (12) is provided with an adjustable clamp (121) for fixing the aerospace pressure storage tank (4); The omnidirectional measuring mechanism (2) comprises an X-axis motion mechanism (21), a Y-axis motion mechanism (22), and a two-axis flip mechanism (23). The Y-axis motion mechanism (22) is slidably mounted on the X-axis motion mechanism (21) along the X-axis direction, and the two-axis flip mechanism (23) is slidably mounted on the Y-axis motion mechanism (22) along the Y-axis direction. The two-axis flip mechanism (23) is used to drive the tank measuring device (3) to perform up and down pitching and circumferential rotation.

2. The measurement system for external inspection of aerospace pressure storage tanks according to claim 1, characterized in that: The measuring system comprises an outer box (5) installed on the ground, and the tank bracket (12) and the omnidirectional measuring mechanism (2) are both installed in the outer box (5).

3. The measurement system for external inspection of aerospace pressure storage tanks according to claim 1, characterized in that: The first rotary drive device (11) is arranged in a trench opened on the ground. The first rotary drive device (11) is provided with a first drive motor (111), a transmission system (112) and an output shaft (113). The first drive motor (111) drives the output shaft (113) to rotate through the transmission system (112). The output shaft (113) is fixedly connected to the tank bracket (12).

4. The measurement system for external inspection of aerospace pressure storage tanks according to claim 3, characterized in that: The transmission system (112) is mounted on a base bracket (1121), and the transmission system (112) includes a coupling (1122), a transmission shaft (1123), a first bevel gear (1124), and a second bevel gear (1125). The first drive motor (111) is fixedly mounted on the base bracket (1121), and a first bearing seat (1126) and a second bearing seat (1127) are mounted on the base bracket (1121). The transmission shaft (1123) and the output shaft (113) are rotatably mounted on the first bearing seat (1126) and the second bearing seat (1127), respectively. The first drive motor (111) is connected to one end of the transmission shaft (1123) via the coupling (1122); the first bevel gear (1124) is fixed to the other end of the transmission shaft (1123); the first bevel gear (1124) and the second bevel gear (1125) are meshed with each other; and the second bevel gear (1125) is fixedly mounted on the output shaft (113).

5. The measurement system for external inspection of aerospace pressure storage tanks according to claim 1, characterized in that: The tank bracket (12) includes a turntable base (122), the turntable base (122) is connected to the first rotary drive device (11), the adjustable clamp (121) is fixedly mounted on the upper surface of the turntable base (122), the adjustable clamp (121) includes at least three groups of adjustment frames (1211) distributed circumferentially and centrally symmetrically, and the aerospace pressure storage tank (4) is placed in a funnel-shaped opening formed between the adjustment frames (1211); Each of the adjustment frames (1211) is provided with an oblique support arm (1212), an insertion rod (1213), a sleeve (1214) and a latch; the bottom of the oblique support arm (1212) is rotatably connected to the turntable base (122); the top of the oblique support arm (1212) is rotatably connected to the insertion rod (1213); the insertion rod (1213) is inserted into the sleeve (1214); the bottom of the sleeve (1214) is rotatably connected to the turntable base (122); the sleeve (1214) and the insertion rod (1213) are both provided with a row of latch holes (1215) with the same spacing; the latch is inserted into the latch holes (1215) of the sleeve (1214) and the insertion rod (1213) that overlap to lock the adjustment frame (1211).

6. The measurement system for external inspection of aerospace pressure storage tanks according to claim 1, characterized in that: The X-axis motion mechanism (21) includes an X-axis track (211), an X-axis driving device (212) and a first slider (213). The X-axis rail (211) is fixedly mounted with an X-axis rack (2111). The X-axis drive device (212) and the Y-axis motion mechanism (22) are both fixedly mounted on the first slider (213), and the X-axis drive device (212) drives the first slider (213) to slide along the X-axis on the X-axis track (211). The X-axis drive device (212) includes a second drive motor and a second drive gear mounted on the output shaft of the second drive motor, and the second drive gear engages with the X-axis rack (2111).

7. The measurement system for external inspection of aerospace pressure storage tanks according to claim 6, characterized in that: The Y-axis motion mechanism (22) includes a Y-axis track (221), a Y-axis driving device (222) and a second slider (223); The Y-axis track (221) is fixedly mounted with a Y-axis rack (2211). The Y-axis driving device (222) and the two-axis flipping mechanism (23) are fixedly mounted on the second slider (223), and the Y-axis driving device (222) drives the second slider (223) to slide along the Y-axis on the Y-axis track (221). The Y-axis driving device (222) includes a third driving motor and a third driving gear mounted on the output shaft of the third driving motor, and the third driving gear is engaged with the Y-axis rack (2211).

8. The measurement system for external inspection of aerospace pressure storage tanks according to claim 1, characterized in that: The Y-axis motion mechanism (22) is driven to slide along the X-axis and / or the two-axis flip mechanism (23) is driven to slide along the Y-axis by a synchronous belt drive mechanism or a ball screw drive mechanism.

9. The measurement system for external inspection of aerospace pressure storage tanks according to claim 7, characterized in that: The two-axis flip mechanism (23) includes a circumferential rotation mechanism (231) and a pitching and swinging mechanism (232). The circumferential rotation mechanism (231) includes a second rotation drive device (2311) and a U-shaped rotating frame (2312); the second rotation drive device (2311) includes a fourth drive motor (2313), a worm wheel (2314), and a worm (2315); the worm (2315) is mounted on the output shaft of the fourth drive motor (2313); the worm (2315) is rotationally connected to the worm wheel (2314), and the worm wheel (2314) is fixedly connected to the rotating frame (2312); The pitching and swinging mechanism (232) includes a fifth driving motor (2321), and the tank body measuring device (3) is mounted on the rotating frame (2312) for vertical rotation. The fifth driving motor (2321) drives the tank body measuring device (3) to perform pitching and swinging on the rotating frame (2312).

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