GB 18163-2000 General technical requirements for self-controlled aircraft amusement machines
Some standard content:
GB18163—2000
This standard is compiled based on the needs of the development of domestic amusement rides. On the basis of YS307—1994 "Technical Conditions and Test Methods for Self-controlled Aircraft Amusement Rides", some clauses are added, some individual clauses are modified, and the effective clauses in YS307-1994 are retained.
This standard replaces YS307—1994 from the date of implementation. This standard is under the jurisdiction of the State Administration of Quality and Technical Supervision. The chapter unit of this standard is the National Amusement Rides Quality Supervision and Inspection Center. The main drafters of this standard are Liu Zhixue, Zhang Xiaoyu and Wang Zhou. rKAoNirKAca-
1 Scope
National Standard of the People's Republic of China
General Technical Conditions for Amusement Rides of Self-controlled Aircraft Category
Specifications of amusement rides agtro fighter category This standard specifies the technical requirements, test methods and inspection rules for self-controlled aircraft amusement rides. GB 18163 -2000
This standard applies to self-controlled aircraft with passenger parts rotating around the central axis and lifting and lowering movements and amusement machines with similar movement forms (hereinafter referred to as self-controlled aircraft).
2 Referenced standards
The provisions contained in the following standards constitute the provisions of this standard through reference in this standard. When this standard is published, the versions shown are valid. All standards will be revised, and parties using this standard should explore the possibility of using the latest versions of the following standards. GB/T699--1999 High-quality carbon structural steel
GB/T983—1995 Stainless steel welding rods
GB/T 985—1988
GB/T 998—-1982
Basic forms and dimensions of weld grooves for manual arc welding and gas shielded welding Basic test methods for low-voltage electrical appliances
Test methods for three-phase asynchronous motors
GB/T 1032—1985
GB/T 2682—19B1
GB/T 3077- 1999
GB/T 4162—1991
Colors of indicator lights and buttons in electrical complete sets Alloy structural steel
Ultrasonic test methods for forged steel bars
GB 4706.1—1998
General safety requirements for household and similar electrical appliances GB/T 5117-—1995
Carbon steel welding rods
GB/T 5119--1995
Low alloy steel welding rods
GB8408—2000Safety of amusement machines and recreational facilities GB50231—1998Construction and acceptance specifications for mechanical equipment installation projects GBJ 65-1983
3 Grounding design specification for industrial and civil power installations JB4730—1994 Pressure penetrator nondestructive testing JB/T5000.12—1998 General technical conditions for type machinery Coating 3 Technical requirements
3.1 Basic provisionsbzxZ.net
3.1.1 The design, manufacture, installation and use of self-controlled aircraft shall comply with the relevant provisions of this standard and GB84.08. 3.1.2 The error between the cockpit lift speed and the rated value shall not exceed 5%. 3.1.3 The rated circumferential speed of the self-controlled aircraft shall not exceed 420m/min; the dynamic load coefficient shall not be less than 1.5. State Administration of Quality and Technical Supervision approved KN KAca on July 31, 2000
2000-11-01 implementation
3.1.4 The rated load is calculated as 70kg per person. GB 181632000
3.1.5 The bearing and contact surface parts with relative motion should be lubricated and lubricant should be added. No oil droplets are allowed. No oil should seep from the parts without relative motion. Test under rated load. 3.1.6 The temperature rise of the cover of the rolling bearing shall not exceed 30℃, and the maximum temperature shall not exceed 65℃. The temperature rise of the oil hole of the sliding bearing shall not exceed 35℃ and the maximum temperature shall not exceed 70℃. Test under rated load after the heating is stable. 3.1.7 The rotating parts and transmission mechanism of the self-controlled aircraft should operate normally, and creeping and abnormal vibration, impact, heating and sound are not allowed.
3.1.8 All parts and their connections are reliable. 3.1.9 Important shafts and pins should be made of materials with mechanical properties not lower than 45# steel. The hardness after quenching and tempering should meet the requirements of GB/T 699 and GB/T 3077. The surface roughness Ra value of the mating surface should not exceed 1.6 μm. 3.1.10 The materials of important parts must have factory certificates. Otherwise, samples should be taken for testing. Their chemical composition and mechanical properties should meet the relevant standards.
3.1.11 Standard electromechanical equipment should be reasonably selected and have product certificates: non-standard electromechanical equipment must be inspected and qualified by the quality inspection department before use.
3.1.12 FRP parts
a) No defects such as poor impregnation, poor curing, bubbles, cut surface delamination, uneven thickness, etc. are allowed; b) No defects such as cracks, damage, obvious repair marks, cloth texture, wrinkles, unevenness, color consistency, etc. are allowed on the surface. The transition at the corner should be smooth:
c) The inner surface should be clean and no glass cloth head should be exposed 1d) The resin content should be controlled at 50%~60%, and the thickness of the gel coat layer should be 0.25~0.5mm; e) The edge of the FRP part should be flat and smooth without delamination, f) When the FRP part is directly connected to the load-bearing part, metal parts should be embedded. The metal embedded parts should be degreased, derusted, cleaned and roughened, g) The mechanical properties of the FRP part should meet the requirements of Table 1. Table 1 Mechanical properties of FRP parts
Tensile strength/MPe
Flexural strength/MPa
Flexural elastic modulus/MPa
Impact toughness/J-cm--
3.1.13 Bolt and pin connection
a) When parts are connected by bolts, measures should be taken to prevent loosening. b) When parts are connected by pins, measures should be taken to prevent falling off. 3.1.14 Welding connection
≥147
≥7.3×10
a) The welding rod used for manual welding shall comply with the provisions of GB/T5117, GB/T 5118 and GB/T 983. The type of welding rod should be adapted to the material of the main component and the type of load on the weld! b) The basic type and size of welding joints shall comply with the provisions of GB/T985; c) The welds shall not have defects such as leaking, burning through, cracks, pores, slag inclusions, incomplete penetration, severe undercuts, etc. All weld bumps, slag, etc. shall be cleaned up.
3.1.15 Important parts and key welds must be inspected by flaw detection. 3.1.16 The cockpit shall not shake during the lifting process, and there shall be no obvious impact vibration during starting and stopping. 3. 1. 17 The inclination angle of the cockpit shall not exceed 5°. -TTKAONi KAca-
GB 18163—2000
3-1.18 The cockpit of the self-controlled aircraft shall leave a safety distance of not less than 500mm from the surrounding obstacles. 3.1.19 In various tests, parts shall not have permanent deformation and damage. Stress testing shall be carried out when necessary. 3.1.20 The life of various wearing parts should be less than 6 months under normal operation. 3.1.21 A nameplate and the production license mark and number must be fixed in a prominent position on the self-controlled aircraft. The nameplate content shall at least include the manufacturer's name, product name, product model or mark, and manufacturing date or number. 3.2 Foundation
3.2.1 The foundation must be constructed according to the design drawings. The foundation of large white-controlled aircraft can only be installed after being inspected and qualified by the relevant quality inspection department. 3.2.2 The foundation should not have abnormal phenomena such as uneven settlement, cracking and loosening that affect the normal operation of the self-controlled aircraft. 3.2.3 When the user unit purchases a large self-digger aircraft, it must provide local meteorological, geographical and geological data for verification by the design and production units.
3.2.4 Anti-loosening measures must be taken for the anchor bolt connection, and it should comply with the provisions of GB50231. 3.3 The inclination tolerance between the slewing bearing surface and the horizontal plane shall not exceed 1/1000. 3.4 The verticality tolerance between the intermediate column and the water surface shall not exceed 1/1000. 3.5 The verticality tolerance between the center line of the cabin support arm and the center line of the pin shaft at the root of the support arm shall not exceed 1/1000. 3.6 The cabin dimensions shall comply with the relevant provisions of 5.8.1 of GB8408-2000. 3.7 Mechanical transmission system
3.7.1 The transmission gears shall comply with the relevant gear standards and have no eccentric meshing and eccentric wear. The contact spot requirements and measurement methods for gear meshing shall refer to GB50231.
3.7.2 Belt and roller chain transmissions shall be appropriately tightened, and their assembly requirements shall comply with the provisions of GB50231. The wear state of the belt shall comply with the provisions of Table 8 of 7.12 of GB 8408-2000. 3.7.3 The brake device must be safe and reliable.
3.7.4 The motor, coupling and reducer should be installed well. The coaxiality and end clearance of the two shafts of the coupling should comply with the provisions of GB50231. The measurement method shall refer to GB50231. 3.8 The hydraulic and pneumatic systems of the self-controlled aircraft shall comply with the provisions of 4.25 in GB8408--2000. 3.9 Electrical system
3.9.1 The voltage level, insulation resistance and grounding resistance shall comply with the relevant provisions in GB8408. The measurement method shall be in accordance with Appendix E of GB4706.1-1998, GB/T1032GBI65 and GB/T998. 3.9.2 The primary and secondary windings of the power transformer with a working voltage not exceeding 50V shall be isolated by insulation equivalent to double insulation or reinforced insulation level. The insulation resistance between the primary and secondary of the transformer shall not be less than 7M, and the insulation resistance between the transformer winding and the metal shell shall not be less than 2M.
3.9.3 The installation of electrical equipment shall comply with the requirements of the relevant national electrical equipment installation engineering construction and acceptance specifications. 3.9.4 The full-load current of the motor shall not be greater than the rated current value of the motor. 3.9.5 Decorative lighting devices that are easily touched by passengers shall use a safe voltage of no more than 50V. 3.9.6 Control system
a) The control system shall meet the working conditions of the amusement machine. b) When automatic control or interlocking control is adopted, each electrical equipment (motor or solenoid valve, etc.) shall be able to be manually controlled separately. c) The control elements shall be sensitive and reliable, and easy to operate. Operation buttons, etc. shall have clear signs, and signal lights, buttons and other color signs shall comply with the provisions of GB/T2682:
d) Electrical switches operated by passengers shall use a safe voltage of no more than 24V. e) Necessary sound and other signaling devices shall be installed. f) Emergency switches must be installed in obvious places on the operating table. The switch button should adopt a raised manual reset type. TIIKANIKAca-
3.9.7 Collector
GB 18163— 2000
a) The brush and slip ring should have good contact and meet the current capacity requirements. The minimum distance between slip rings is 8mm, and there should be no breakdown or flashover in the slip ring withstand voltage test;
b) The exposed collector must be equipped with a rain cover. 3.10 Safety device
3.10.1 The cockpit lifting support arm should be equipped with a limit device. 3.10.2 Non-enclosed cockpits should be equipped with safety belts and handles with a width of more than 30mm and sufficient strength. 3.10.3 When the power supply is suddenly cut off or the equipment fails, measures should be taken to lower the air cockpit to the ground. 3.10.4 The cockpit traction device must have insurance measures. 3.11 Appearance and Painting
3.11.1 The shape, decorations and paint patterns of the self-controlled aircraft should be beautiful, bright and eye-catching. There should be no bumps, cracks and roughness that affect the appearance.
3.11.2 The surface of the electroplated parts should be smooth, bright and even. There should be no defects such as delamination, bubbles, obvious scratches and exposed bottom. 3.11-3 The exposed metal parts should not be rusted. 3.11.4 Painting
a) Rust and other contaminants must be removed before painting, and the quality of manual rust removal must reach St2 level in JB/T5000.12; 6) The inner surface of the open metal components should be coated with 60-80% anti-rust paint; the outer surface of the metal parts must be painted or sprayed with plastic, the coating thickness should be 100-150μm: the plastic layer thickness should be 200-500μm; c) The outer surface of the fiberglass must be treated before spraying; ) The coating should not have obvious defects such as hanging, wrinkling, falling off, cracks and dirt. 3.12 The placement of safety fences, platforms, stairs and operating rooms shall comply with the provisions of 4.13.4.18, 5.7 and 5.8.2 in GB8408-2000.
4 Test methods
4.1 General requirements
4.1.1 All new products, products transferred to other factories and products with major improvements shall be tested in accordance with this standard before leaving the factory. 4.1.2 Formal product identification, issuance of production licenses, quality supervision spot checks and safety inspections shall be tested in accordance with this standard. Test items may be increased or decreased according to different test purposes. 4.2 Test conditions
4.2.1 The wind speed during the test shall not exceed 15m/s
4.2.2 If there are no special requirements, the ambient temperature during the test is generally between -10 and 35 degrees Celsius. The relative humidity of the environment is not more than 85%. 4.2.3 The error between the test load and its rated value shall not exceed ±2%. 4.2.4 The production unit shall provide the inspection data, records, drawings and technical documents of the product. The various tests specified in this standard can only be carried out after the inspection department confirms that the product is qualified.
4.2.5 For self-controlled aircraft with special requirements, additional test items may be considered. 4.3 Test instruments and measuring tools
4.3.1 According to the test requirements, select test instruments and measuring tools of corresponding accuracy. 4.3.2 The instruments, meters and other measuring tools used for the test must be qualified by the legal metrology department and must be checked and calibrated before and after the test. The conversion element should be calibrated before and after the test, and its deviation must be within the specified range. 4.4 The inspection of safety devices shall comply with the provisions of 3.10 of this standard. 4.5 The inspection of the foundation, intermediate column, support arm, cockpit, platform, ladder, safety fence operating room, appearance and installation of the self-controlled aircraft shall comply with the relevant provisions of Chapter 3 of this standard.
4.6 No-load test
GB 18163—2000
4.6.1 Carry out manual and automatic tests for no less than 3 times each. 4.6.2 Test continuously for 8 hours according to actual working conditions.
4.7 Full load test
4.7.1 Load evenly according to rated load.
4. 7.2 Test continuously for 10 times according to actual working conditions, 8 hours per day. 4.8 Eccentric load test
4.8.1 Add rated load to half of the cabin. 4.8.2 Test continuously for 3 times according to actual working conditions. 4.9 During the no-load, full-load and eccentric load tests, it should operate normally and comply with the relevant provisions of 3.1 of this standard. The mechanical transmission system, hydraulic and pneumatic system and electrical system should comply with the provisions of 3.7, 3.8 and 3.9 of this standard respectively. 4.10 Stress test
4.10.1 Test conditions are shown in Table 2.
Table 2 Test conditions
4.10.2 Test method
Additional conditions
Rated load
a) Before testing, the test should be carried out under the rated load. b) The strain value of each point should be measured according to the working conditions listed in Table 2. c) Each working condition should be repeated for no less than 3 times. 4.10.3 Stress value
Tested parts
Supporting hip, traction rod, pin
a) The stress generated under the action of deadweight should be provided by the relevant units with its calculated value, test method
Static stress measurement
Dynamic stress measurement
b) The stress value of each measuring point should be the sum of the test stress value under the load and the calculated stress value under the deadweight. 4.10.4 Safety criterion for stress value
Safety factor = breaking strength of material
Maximum stress at measuring point
The maximum stress value at each measuring point shall comply with the safety factor value given in Table 3 of 5.4 of GB8408--2000. 4.11 Non-photographic flaw detection
4.11.1 Important locking shafts of white-controlled aircraft must be 100% ultrasonically and magnetically (or penetrantly) inspected. 4.11.2 Important welds such as the supporting plate connecting the supporting arm and the cockpit must be 100% magnetically (or penetrantly) inspected. 4.11.3 The ultrasonic flaw detection method and quality assessment shall be carried out in accordance with the relevant provisions of GB/T4162. The inspection quality level shall not be lower than Grade A. 4.11.4 Magnetic particle flaw detection method and quality assessment shall be carried out in accordance with the relevant provisions of JB4730. The inspection quality level shall not be lower than Grade. 4.11.5 Penetrant testing methods and quality assessment shall be carried out in accordance with the relevant provisions of JB4730. The inspection quality level shall not be lower than the mutual level. 4.12 Disassembly and inspection requirements
The equipment with problems should be disassembled and inspected, and the disassembly and inspection situation should be recorded in detail. The problems found should be studied in time to determine the causes. The records can be made in the form of text and photos.
4.13 Test report
After each test is completed, a test report with clear conclusions and in compliance with relevant regulations shall be written. 5 Inspection rules
5.! Product defects that do not meet the requirements of the standards are divided into major defects and minor defects. The major defects are shown in Table 3. If each sample has more than one (including one) major defect or more than five (including five) minor defects, it is a defective product. Table 3 Major defects of self-controlled aircraft amusement machines Standard item number
3-9-1
Improper operation, abnormal phenomena
No flaw detection
Parts have permanent deformation or damage
Uneven foundation settlement and cracking
Defect content
Insulation resistance and grounding resistance do not meet the requirements
No safety belt and handle
No safety measure
5.2 After rework, the defective products must meet the requirements of qualified products, otherwise they should be scrapped. GB18163-2000 (General Technical Specifications for Self-Controlled Aircraft Amusement Machines) Amendment No. 1
This amendment was approved by the National Standardization Administration on September 4, 2002 with the document [2002] No. 46 of the National Standardization Administration, and will be implemented from December 1, 2002.
Standard Clauses
3.1.12b
4.11.1
··Color inconsistency and other defects
Important locking shaft of self-controlled aircraft -.·
TKANiKAca
Changed to
·Color inconsistency and other defects,
Important pin shaft of self-controlled aircraft·
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