Falling object prevention and control device used in test operation of spaceflight launching site
By designing an automated falling object control device, which uses visual sensors and motor-controlled rotating hinges to adjust the position of the cargo bag, the problem of inconvenience in manual falling object prevention during space launch site testing operations has been solved, thus improving safety and reliability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- CHINESE PEOPLES LIBERATION ARMY UNIT 63601
- Filing Date
- 2025-07-01
- Publication Date
- 2026-04-17
AI Technical Summary
In current space launch site testing operations, fall protection measures rely on manual operation, which is inconvenient to implement in confined or high-altitude environments, resulting in insufficient safety and reliability.
A fall protection device comprising a locking element, an extension element, a cargo bag, and a rotating hinge was designed. It combines a vision sensor and a motor to achieve automatic control. The position of the cargo bag is adjusted by the rotating hinge to prevent falling objects, thus providing automated protection.
It has enabled unmanned control of falling objects during test operations at space launch sites, reducing risks, improving operational safety and reliability, and meeting the control requirements in both general and special environments.
Smart Images
Figure CN224131319U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of falling object control technology used in conjunction with testing operations at aerospace launch sites, and specifically relates to a falling object control device used in testing operations at aerospace launch sites. Background Technology
[0002] A space launch site (or astrodrome) is a specific area used to launch spacecraft carrying space launch vehicles. It possesses a complete set of facilities and equipment for assembling, storing, and testing spacecraft and launch vehicles, measuring flight trajectories, sending control commands, and receiving and processing telemetry information. It completes all the testing, assembly, and launch work for space launch vehicles, spacecraft, payloads, and astronaut systems, and is an important component of the space system. Some space launch sites also include the drop zone for booster rockets or launch vehicles after the first stage of their mission and the spacecraft recovery and landing site.
[0003] Testing operations at a space launch site involve numerous tasks. If extraneous objects or other items fall during the testing process, or even if objects fall from a height, it will affect the smooth implementation of the space launch mission. Therefore, falling object prevention measures play a very important role in the testing operations at a space launch site. They must be able to ensure the safety of the testing environment and reduce the risk of falling objects injuring personnel or damaging products.
[0004] Currently, the existing fall protection measures at space launch sites typically involve using homemade cloth bags, which are usually carried out by operators by hand. This consumes a certain amount of manpower, and the existing method is not convenient for fall protection when operating in confined spaces or at high altitudes. Therefore, there is an urgent need for a fall protection device that can meet the requirements of the special working environment during space launch site testing operations. Utility Model Content
[0005] To address the quality and safety requirements for falling object control during space launch site testing operations, as well as the safety and reliability of the testing process, and to solve the problem of unmanned target falling object control during space launch site testing operations, this utility model proposes a falling object control device for space launch site testing operations based on the quality requirements of space launch site testing operations. This device can meet the unmanned requirements of general fall prevention measures at space launch sites, can be used under special working conditions, and has certain automatic control functions, thereby improving the safety and reliability of the testing operation process.
[0006] The objective of this utility model is specifically achieved through the following technical solution:
[0007] This utility model discloses a falling object control device for test operations at a space launch site, comprising: a locking component 10, an extension component 20, a cargo bag 30, and a rotating hinge 13;
[0008] The bottom outer side of the locking member 10 is connected to the rotating hinge 13; the extension member 20 connects the rotating hinge 13 to the opening of the carrying bag 30 through the hinges 22 at both ends.
[0009] The locking member 10 is snapped and fixed to the inherent components of the space launch site. The rotating hinge 13 connected to the bottom outer side of the locking member 10 rotates to adjust the angle and position of the extension member 20. The extension member 20 adjusts the position of the cargo bag 30 through the hinges at both ends, so that the cargo bag 30 is placed under the target falling object.
[0010] Furthermore, the locking element 10 includes a frame 11 and a limiting rod 12;
[0011] The frame 11 has a hollow structure and is formed by rigidly connecting the first side column with the symmetrical upper and lower crossbeams.
[0012] The limiting rod 12 is a T-shaped threaded rod. The length of the T-shaped threaded rod is greater than the height of the first side column and is adapted to the threaded through hole of the upper crossbeam of the frame 11. After the limiting rod 12 passes through the threaded through hole, it is rigidly connected to the limiting piece 120, and the limiting piece 120 is built into the frame 11.
[0013] The limiting plate 120, the first side column 114 and the lower crossbeam 110 form a first snap-fit structure. After the target inherent component of the space launch site is placed into the first snap-fit structure, the height of the limiting plate 120 is adjusted by rotating the limiting rod 12 to snap the target inherent component.
[0014] The inner side of the first snap-fit structure is covered with anti-slip rubber.
[0015] As another embodiment of this utility model, the free end of the lower crossbeam 110 of the frame 11 also has a second side column 115, the height of the second side column 115 being less than the height of the first side column 114.
[0016] The limiting plate 120, the first side column 114, the lower crossbeam 110 and the second side column 115 constitute the second snap-fit structure. After the target inherent component of the space launch site is placed into the second snap-fit structure, the height of the limiting plate 120 is adjusted by rotating the limiting rod 12 to snap the target inherent component.
[0017] The inner side of the second snap-fit structure is covered with anti-slip rubber.
[0018] Furthermore, the rotating hinge 13 is installed on the outside of the lower crossbeam of the frame 11 of the locking member 10, and includes a hinge shaft 131, a rotating disk 132 and a pressing disk 133.
[0019] The hinge shaft 131 is connected to the lower crossbeam of the frame 11 by passing through the center of the rotating disk 132 via a thread on the shaft, so that the rotating disk 132 is tightly attached to the outer side of the lower crossbeam;
[0020] The clamping plate 133 is installed on the hinge shaft 131 via an internal thread to clamp the rotating plate 132; the rotating plate 132 can rotate normally after being clamped.
[0021] Furthermore, the edge of the rotating disk 132 has an extended end, which is at a preset angle to the edge of the rotating disk 132 and is not in close contact with the outer side of the lower crossbeam. The free end of the extended end is connected to the hinge 22 at one end of the extension member 20.
[0022] Furthermore, the extension member 20 is composed of one or more load-bearing rods 21 connected in sequence, and each load-bearing rod 21 has a hinge 22 at both ends; wherein the hinge 22 has at least two degrees of freedom.
[0023] Furthermore, the carrying bag 30 includes a support frame 31 and a load-bearing member 32;
[0024] The support frame 31 is a ring structure and is installed at the top of the load-bearing member 32 to form the opening of the carrying bag 30; the bottom of the load-bearing member 32 is sealed to form the carrying part of the carrying bag 30.
[0025] Preferably, the support frame 31 is made of a material with a certain degree of hardness, including but not limited to iron wire, copper wire, or aluminum wire. The load-bearing component 32 is made of a soft material that is not easily scratched.
[0026] As another embodiment of this utility model, it also includes an adjustment device, which includes a processing component 111, a motor 112, a buzzer 113, a vision sensor 311, and a distance sensor 23.
[0027] The processing component 111 and the buzzer 113 are built into the hollow structure within the frame 11 of the locking component 10; the motor 111 is connected to the rotating hinge 13, and the motor 112 drives the rotating hinge 13 to rotate clockwise or counterclockwise around the hinge axis 131.
[0028] The distance sensor 23 is mounted on the hinges 22 at both ends of the extension member 20 and is used to sense the straight-line distance between the hinges 22 at both ends of the extension member 20.
[0029] The visual sensor 311 is mounted on the support frame 31 at the opening of the cargo bag 30 and is used to sense the movement above the cargo bag 30 and the distance between the visual sensor 311 and the center of the movement where the movement occurs.
[0030] The processing component 111 is connected to the motor 112, the buzzer 113, the vision sensor 311 and the distance sensor 23 via cables, and can transmit signals bidirectionally through the cables;
[0031] When the vision sensor 311 detects movement above the cargo bag 30, it senses the distance from the center of movement and converts this distance into an electrical signal, which is then transmitted to the processing component 111 via a cable. Simultaneously, the distance sensor senses the straight-line distance between the hinges at both ends of the extension member and converts this straight-line distance into an electrical signal, which is then transmitted to the processing component 111 via a cable. The processing component 111 obtains a processing result based on the judgment conditions and converts it into an electrical signal. Based on the judgment conditions corresponding to the processing result, it selects to transmit the signal via a cable to the motor 112 to drive the rotating hinge 13 to rotate clockwise or counterclockwise; or to transmit the rotational signal to the buzzer 113 for an alarm.
[0032] Furthermore, the number of vision sensors 311 is even, and the line connecting the center of the hinge 22 connecting the bag 30 and one end of the extension member 20 and the center of the support frame 31 on the opening of the bag 30 is the axis of symmetry O0, so that the vision sensors 311 are symmetrically distributed on the support frame 31.
[0033] The determination conditions for the processing component 111 include a first determination condition and a second determination condition; wherein the first determination condition is:
[0034] when and ;
[0035] ;
[0036] Where α is the rotational radius of the pivot hinge, and L n+ L n- These are the two sensing distances corresponding to two symmetrical vision sensors, max(L) n+ L n- ) represents the maximum distance perceived by the two symmetrical vision sensors, min(L) n+ L n- L is the minimum distance perceived by two symmetrical vision sensors. x d is the straight-line distance between the hinges at both ends of the extension member sensed by the distance sensor, d is the diameter of the support frame of the cargo bag, and U is the output voltage of the processing components to the buzzer. th This refers to the threshold voltage of the buzzer.
[0037] When L n+ >L n- When α is positive, the rotating hinge rotates clockwise; when L n+ <L n- When α is negative, the rotating hinge rotates counterclockwise.
[0038] The second judgment condition is: when or ;
[0039] ;
[0040] When U<U th When U ≥ U, the buzzer does not emit a sound; when U ≥ U th At that time, the buzzer sounds.
[0041] If the maximum sensing distance difference of a single sensor does not exceed the diameter of the support frame 31, the required rotation angle of the rotating hinge 13 is calculated based on the first judgment condition and converted into an electrical signal, which is then output to the motor 112 via a cable, thereby causing the motor 112 to work. If the electrical signal is positive, the motor drives the rotating hinge to rotate clockwise, positioning the bag below the center of motion. If the electrical signal is negative, the motor drives the rotating hinge to rotate counterclockwise, positioning the bag below the center of motion. At this time, the output voltage of the processing component 111 is less than the buzzer threshold voltage, and the buzzer 113 does not emit a sound.
[0042] If the maximum sensing distance difference of a single sensor exceeds the diameter of the support frame 31, the output voltage of the processing component 111 will be greater than the buzzer threshold voltage according to the second judgment condition. The buzzer 113 will sound to remind the operator to move the extension piece manually so that the cargo bag is moved below the movement behavior. At this time, the motor 112 will not work and the rotating hinge will not rotate.
[0043] Beneficial effects:
[0044] This invention proposes a falling object control device for test operations at a space launch site, which realizes unmanned falling object control measures in test operations at a space launch site, reduces the risk of test operations at a space launch site, improves the work efficiency of test operators, can meet the quality and safety requirements of falling object control in test operations under both general and special working environments, and improves the safety and reliability of the test operation process. Attached Figure Description
[0045] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments.
[0046] Figure 1This is a schematic diagram of a falling object control device for test operations at a space launch site, provided by an embodiment of this utility model.
[0047] Figure 2 This is a schematic diagram of the locking component structure provided in one embodiment of the present invention.
[0048] Figure 3 This is a schematic diagram of another structure of the locking member provided in one embodiment of the present utility model.
[0049] Figure 4 This is a schematic diagram of the frame structure provided in one embodiment of the present utility model.
[0050] Figure 5 This is a schematic diagram of the extension member structure provided in one embodiment of the present utility model.
[0051] Figure 6 This is a schematic diagram of the structure of a cargo bag provided in one embodiment of this utility model.
[0052] Figure 7 This is a schematic diagram of a rotating hinge structure provided in one embodiment of the present invention.
[0053] Figure 8 This is a schematic diagram of the installation of a vision sensor according to an embodiment of the present invention.
[0054] Figure 9 This is a schematic diagram showing the positional relationship between the visual sensor and the center of motion behavior provided in one embodiment of this utility model. Detailed Implementation
[0055] like Figure 1-9 As shown, this utility model embodiment provides a falling object control device for test operations at a space launch site, including: a locking member 10, an extension member 20, a cargo bag 30, and a rotating hinge 13;
[0056] The bottom outer side of the locking member 10 is connected to the rotating hinge 13; the extension member 20 connects the rotating hinge 13 to the opening of the carrying bag 30 through the hinges 22 at both ends.
[0057] The locking member 10 is snapped and fixed to the inherent components of the space launch site. The rotating hinge 13 connected to the bottom outer side of the locking member 10 rotates to adjust the angle and position of the extension member 20. The extension member 20 adjusts the position of the cargo bag 30 through the hinges at both ends, so that the cargo bag 30 is placed under the target falling object.
[0058] like Figure 2 As shown, the locking element 10 includes a frame 11 and a limiting rod 12;
[0059] The frame 11 has a hollow structure and is formed by rigidly connecting the first side column with the symmetrical upper and lower crossbeams.
[0060] The limiting rod 12 is a T-shaped threaded rod. The length of the T-shaped threaded rod is greater than the height of the first side column and is adapted to the threaded through hole of the upper crossbeam of the frame 11. After the limiting rod 12 passes through the threaded through hole, it is rigidly connected to the limiting piece 120, and the limiting piece 120 is built into the frame 11.
[0061] The limiting plate 120, the first side column 114 and the lower crossbeam 110 form a first snap-fit structure. After the target inherent component of the space launch site is placed into the first snap-fit structure, the height of the limiting plate 120 is adjusted by rotating the limiting rod 12 to snap the target inherent component.
[0062] The inner side of the first snap-fit structure is covered with anti-slip rubber.
[0063] As another solution of this utility model, such as Figure 3 As shown, the free end of the lower crossbeam 110 of the frame 11 also has a second side column 115, the height of the second side column 115 being less than the height of the first side column 114.
[0064] The limiting plate 120, the first side column 114, the lower crossbeam 110 and the second side column 115 constitute the second snap-fit structure. After the target inherent component of the space launch site is placed into the second snap-fit structure, the height of the limiting plate 120 is adjusted by rotating the limiting rod 12 to snap the target inherent component.
[0065] The inner side of the second snap-fit structure is covered with anti-slip rubber.
[0066] like Figure 6 As shown, the rotating hinge 13 is installed on the outside of the lower crossbeam of the frame 11 of the locking member 10, and includes a hinge shaft 131, a rotating disk 132 and a pressing disk 133;
[0067] The hinge shaft 131 is connected to the lower crossbeam of the frame 11 by passing through the center of the rotating disk 132 via a thread on the shaft, so that the rotating disk 132 is tightly attached to the outer side of the lower crossbeam;
[0068] The clamping plate 133 is installed on the hinge shaft 131 via an internal thread to clamp the rotating plate 132; the rotating plate 132 can rotate normally after being clamped.
[0069] The edge of the rotating disk 132 has an extended end, which is at a preset angle to the edge of the rotating disk 132 and is not in close contact with the outer side of the lower crossbeam. The free end of the extended end is connected to the hinge 22 at one end of the extension member 20.
[0070] like Figure 4As shown, the extension member 20 is composed of one or more load-bearing rods 21 connected in sequence, and each load-bearing rod 21 has a hinge 22 at both ends; wherein the hinge 22 has at least two degrees of freedom.
[0071] like Figure 5 As shown, the cargo bag 30 includes a support frame 31 and a load-bearing member 32;
[0072] The support frame 31 is a ring structure and is installed at the top of the load-bearing member 32 to form the opening of the carrying bag 30; the bottom of the load-bearing member 32 is sealed to form the carrying part of the carrying bag 30.
[0073] Preferably, the support frame 31 is made of a material with a certain degree of hardness, including but not limited to iron wire, copper wire, or aluminum wire. The load-bearing component 32 is made of a soft material that is not easily scratched.
[0074] As another embodiment of this utility model, it also includes an adjustment device, which includes a processing component 111, a motor 112, a buzzer 113, a vision sensor 311, and a distance sensor 23.
[0075] Optionally, the processing component 111 may include, but is not limited to, an 8051 microcontroller, a PIC microcontroller, or an MSP430 microcontroller.
[0076] The models of motor 112 include, but are not limited to: ZYT AC motor, RF-300CA DC motor, or N20 DC motor, etc.
[0077] The models of buzzer 113 include, but are not limited to: FMQ-A1 buzzer or 12095 buzzer, etc.
[0078] The models of the vision sensor 311 include, but are not limited to: Keyence IV-500CA or Keyence IV3-600MA, etc.
[0079] The models of distance sensor 23 include, but are not limited to: HC-SR04 or HG-C1200, etc.
[0080] The processing component 111 and the buzzer 113 are built into the hollow structure within the frame 11 of the locking component 10; the motor 111 is connected to the rotating hinge 13, and the motor 112 drives the rotating hinge 13 to rotate clockwise or counterclockwise around the hinge axis 131.
[0081] The distance sensor 23 is mounted on the hinges 22 at both ends of the extension member 20 and is used to sense the straight-line distance between the hinges 22 at both ends of the extension member 20.
[0082] The visual sensor 311 is mounted on the support frame 31 at the opening of the cargo bag 30 and is used to sense the movement above the cargo bag 30 and the distance between the visual sensor 311 and the center of the movement where the movement occurs.
[0083] The processing component 111 is connected to the motor 112, the buzzer 113, the vision sensor 311 and the distance sensor 23 via cables, and can transmit signals bidirectionally through the cables;
[0084] When the vision sensor 311 detects movement above the cargo bag 30, it senses the distance from the center of movement and converts this distance into an electrical signal, which is then transmitted to the processing component 111 via a cable. Simultaneously, the distance sensor senses the straight-line distance between the hinges at both ends of the extension member and converts this straight-line distance into an electrical signal, which is then transmitted to the processing component 111 via a cable. The processing component 111 obtains a processing result based on the judgment conditions and converts it into an electrical signal. Based on the judgment conditions corresponding to the processing result, it selects to transmit the signal via a cable to the motor 112 to drive the rotating hinge 13 to rotate clockwise or counterclockwise; or to transmit the rotational signal to the buzzer 113 for an alarm.
[0085] like Figures 7 to 8 As shown, there is an even number of vision sensors 311. The line connecting the center of the hinge 22 connecting the bag 30 and one end of the extension member 20 and the center of the support frame 31 on the opening of the bag 30 is the axis of symmetry O0, and the vision sensors 311 are symmetrically distributed on the support frame 31.
[0086] In this embodiment, the visual sensors 311 symmetrically distributed on the support frame 31 are defined as C1+, C1-, C2+, C2-, ..., Cn+, Cn-, where the first visual sensor C1+ and the second visual sensor C1- are symmetrical with respect to the axis of symmetry O0, and so on; the distances sensed by each visual sensor are L1+, L1-, L2+, L2-, ..., Ln+, Ln-.
[0087] The motion behavior generally refers to the actions of the operator when operating with hands or tools, and the center of motion behavior refers to the physical center of the motion behavior, which is generally the center of mass. The purpose of defining motion behavior and the center of motion behavior is to enable the visual sensor to perceive the test operation position at the space launch site so that the cargo bag 30 can always be directly below the test operation position.
[0088] The determination conditions for the processing component 111 include a first determination condition and a second determination condition; wherein the first determination condition is:
[0089] when and ;
[0090] ;
[0091] Where α is the rotational radius of the pivot hinge, and L n+ L n- These are the two sensing distances corresponding to two symmetrical vision sensors, max(L) n+ L n- ) represents the maximum distance perceived by the two symmetrical vision sensors, min(L) n+ L n- L is the minimum distance perceived by two symmetrical vision sensors. x d is the straight-line distance between the hinges at both ends of the extension member sensed by the distance sensor, d is the diameter of the support frame of the cargo bag, and U is the output voltage of the processing components to the buzzer. th This refers to the threshold voltage of the buzzer.
[0092] When L n+ >L n- When α is positive, the rotating hinge rotates clockwise; when L n+ <L n- When α is negative, the rotating hinge rotates counterclockwise.
[0093] The second judgment condition is: when or ;
[0094] ;
[0095] When U<U th When U ≥ U, the buzzer does not emit a sound; when U ≥ U th At that time, the buzzer sounds.
[0096] If the maximum sensing distance difference of a single sensor does not exceed the diameter of the support frame 31, the required rotation angle of the rotating hinge 13 is calculated based on the first judgment condition and converted into an electrical signal, which is then output to the motor 112 via a cable, thereby causing the motor 112 to work. If the electrical signal is positive, the motor drives the rotating hinge to rotate clockwise, positioning the bag below the center of motion. If the electrical signal is negative, the motor drives the rotating hinge to rotate counterclockwise, positioning the bag below the center of motion. At this time, the output voltage of the processing component 111 is less than the buzzer threshold voltage, and the buzzer 113 does not emit a sound.
[0097] If the maximum sensing distance difference of a single sensor exceeds the diameter of the support frame 31, the second judgment condition causes the output voltage of the processing component 111 to exceed the buzzer threshold voltage. The buzzer 113 then sounds, reminding the operator to manually move the extension piece to position the bag below the movement. At this time, the motor 112 does not operate, and the rotating hinge does not rotate. The function of the buzzer is to remind the operator to manually move the extension piece to position the bag below the movement.
[0098] More preferably, when using this device, at least two fall protection devices or other fall prevention measures can be set up for secondary protection to prevent it from falling beyond its maximum load-bearing capacity under primary protection.
[0099] Beneficial effects:
[0100] This invention proposes a falling object control device for test operations at a space launch site, which realizes unmanned falling object control measures in test operations at a space launch site, reduces the risk of test operations at a space launch site, improves the work efficiency of test operators, can meet the quality and safety requirements of falling object control in test operations under both general and special working environments, and improves the safety and reliability of the test operation process.
[0101] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.
Claims
1. A debris mitigation device for use in a space launch site test operation, comprising: include: Locking elements, extension elements, cargo bags, and swivel hinges; The bottom outer side of the locking element is connected to the rotary hinge; The extension piece connects the rotating hinge to the opening of the cargo bag via hinges at both ends. The locking component is snapped and fixed to an inherent component of the space launch site. The rotating hinge connected to the bottom outer side of the locking component can be rotated to adjust the angle and position of the extension component. The extension component adjusts the position of the cargo bag through the hinges at both ends, so that the cargo bag is placed below the target falling object.
2. A debris mitigation device for use in the testing operations of a space launch site as defined in claim 1, wherein, The locking component includes a frame and a limiting rod; The frame has a hollow structure and is formed by rigidly connecting the first side column with symmetrical upper and lower crossbeams. The limiting rod is a T-shaped threaded rod, the length of which is greater than the height of the first side column, and it is adapted to the threaded through hole of the upper crossbeam of the frame; after the limiting rod passes through the threaded through hole, it is rigidly connected to the limiting piece, and the limiting piece is built into the frame; The limiting plate, the first side column and the lower crossbeam form the first snap-fit structure. After the target component of the space launch site is placed into the first snap-fit structure, the height of the limiting plate is adjusted by rotating the limiting rod to snap the target component. The inner side of the first snap-fit structure is covered with anti-slip rubber.
3. A debris mitigation device for use in the testing operations of a space launch site as defined in claim 2, wherein, The free end of the lower crossbeam of the frame also has a second side column, the height of which is less than the height of the first side column. The limiting plate, the first side column, the lower crossbeam and the second side column constitute the second snap-fit structure. After the target component of the space launch site is placed into the second snap-fit structure, the height of the limiting plate is adjusted by rotating the limiting rod to snap the target component. The inner side of the second snap-fit structure is covered with anti-slip rubber.
4. A ballistic protection device for use in the testing operations of a space launch site according to one of claims 1 to 3, characterized in that, The rotary hinge is installed on the outside of the lower crossbeam of the frame of the locking member, and includes a hinge shaft, a rotating disk, and a clamping disk; The hinge shaft is connected to the lower crossbeam of the frame by passing through the center of the rotating disk via a thread on the shaft, so that the rotating disk is tightly attached to the outer side of the lower crossbeam; The clamping plate is installed on the hinge shaft via an internal thread to clamp the rotating disk; the rotating disk can rotate normally after being clamped.
5. A ballistic protection device for use in the testing operations of a space launch site according to claim 4, characterized in that, The edge of the rotating disk has an extended end, which is at a preset angle to the edge of the rotating disk and is not in close contact with the outer side of the lower crossbeam. The free end of the extended end is connected to a hinge at one end of the extension member.
6. A debris mitigation device for use in the testing operations of a space launch site as claimed in claim 1 or 5, wherein, The extension member is composed of one or more load-bearing rods connected in sequence, each load-bearing rod having hinges at both ends; wherein each hinge has at least two degrees of freedom.
7. A debris mitigation device for use in the testing operations of a space launch facility as in claim 1, wherein, The cargo bag includes a support frame and load-bearing components; The support frame is a ring structure and is installed at the top of the load-bearing member to form the opening of the bag; the bottom of the load-bearing member is sealed to form the carrying part of the bag.
8. A ballistic protection device for use in the testing operations of a space launch site according to claim 1, characterized in that, It also includes an adjustment device, which includes processing components, a motor, a buzzer, a vision sensor, and a distance sensor; The processing components and buzzer are built into the hollow structure within the frame of the locking member; the motor is connected to the rotating hinge, and the motor drives the rotating hinge to rotate clockwise or counterclockwise around the hinge axis; The distance sensor is installed on the hinges at both ends of the extension member to sense the straight-line distance between the hinges at both ends of the extension member. The visual sensor is mounted on a support frame at the opening of the cargo bag and is used to sense the movement above the cargo bag and the distance between the visual sensor and the center of the movement. The processing components are connected to the motor, buzzer, vision sensor and distance sensor respectively via cables, and can transmit signals bidirectionally through the cables; When the vision sensor detects movement above the cargo bag, it measures the distance to the center of the movement and converts this distance into an electrical signal, which is then transmitted to the processing component via a cable. Simultaneously, the distance sensor measures the straight-line distance between the hinges at both ends of the extension member and converts this straight-line distance into an electrical signal, which is also transmitted to the processing component via a cable. The processing component determines the processing result based on the judgment conditions and converts it into an electrical signal. Based on the judgment conditions corresponding to the processing result, it selects whether to transmit the signal via cable to the motor to drive the rotating hinge to rotate clockwise or counterclockwise, or to transmit the rotational signal to the buzzer for an alarm.
9. A ballistic protection device for use in the testing operations of a space launch site according to claim 8, characterized in that, The number of vision sensors is even. The straight line connecting the hinge connecting one end of the bag and the extension member and the center of the support frame on the opening of the bag is the axis of symmetry, and the vision sensors are symmetrically distributed on the support frame.
10. A debris mitigation device for use in the testing operations of a space launch site as claimed in claim 8 or 9, characterised in that, The determination conditions for the processed components include a first determination condition and a second determination condition; wherein, The first judging condition is that when and ; ； Where α is the rotational radius of the pivot hinge, and L n+ L n- These are the two sensing distances corresponding to two symmetrical vision sensors, max(L) n+ L n- ) represents the maximum distance perceived by the two symmetrical vision sensors, min(L) n+ L n- L is the minimum distance perceived by two symmetrical vision sensors. x d is the straight-line distance between the hinges at both ends of the extension member sensed by the distance sensor, d is the diameter of the support frame of the cargo bag, and U is the output voltage of the processing components to the buzzer. th This refers to the threshold voltage of the buzzer. When L n+ >L n- When α is positive, the rotating hinge rotates clockwise; when L n+ <L n- When α is negative, the rotating hinge rotates counterclockwise. The second determination condition is that when or ; ； When U < U th the buzzer does not sound; when U ≥ U th the buzzer sounds. If the maximum sensing distance difference of a single sensor does not exceed the diameter of the support frame, the required rotation angle of the rotating hinge is calculated based on the first judgment condition and converted into an electrical signal, which is then output to the motor via a cable, thereby enabling the motor to operate. If the electrical signal is positive, the motor drives the rotating hinge to rotate clockwise, positioning the bag below the center of motion. If the electrical signal is negative, the motor drives the rotating hinge to rotate counterclockwise, positioning the bag below the center of motion. At this time, the output voltage of the processing components is less than the buzzer threshold voltage, and the buzzer does not emit a sound. If the maximum sensing distance difference of a single sensor exceeds the diameter of the support frame, the output voltage of the processing component will be made greater than the buzzer threshold voltage by the second judgment condition. The buzzer will then sound to remind the operator to move the extension piece manually so that the cargo bag is moved below the movement behavior. At this time, the motor will not work and the rotating hinge will not rotate.