WO2017171688A1 - Method of external suspension installation diagnostics and repair as required of for small loads - Google Patents
Method of external suspension installation diagnostics and repair as required of for small loads Download PDFInfo
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- WO2017171688A1 WO2017171688A1 PCT/UA2016/000130 UA2016000130W WO2017171688A1 WO 2017171688 A1 WO2017171688 A1 WO 2017171688A1 UA 2016000130 W UA2016000130 W UA 2016000130W WO 2017171688 A1 WO2017171688 A1 WO 2017171688A1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06Q—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES; SYSTEMS OR METHODS SPECIALLY ADAPTED FOR ADMINISTRATIVE, COMMERCIAL, FINANCIAL, MANAGERIAL OR SUPERVISORY PURPOSES, NOT OTHERWISE PROVIDED FOR
- G06Q10/00—Administration; Management
- G06Q10/20—Administration of product repair or maintenance
Definitions
- the utility model relates to the field of aviation and aircraft repair and modernization technology, including the method of external suspension diagnosing and repair as per technical state for small loads of aircrafts of 24, 26, 32 types with modifications. Due to significant investments required for new aircraft development or purchases of upgraded, it is important to maintain the existing aviation equipment in operation state and possibility of extending the operational life by repairs as per technical state with upgradeability.
- External suspension installation for small loads of aircraft of An-24, 26, 32 types provides suspension of cargoes with 50 to 500 kg weights on the aircraft.
- Installations contain pylons, beam holders of BDZ-34 type, an electrical cargo dropping control system with beam holders.
- Pylons are installed outside the fuselage, two on each side in the area of frames Nos. 15-16 and 21-22. Pylons are an intermediate link between the holder and the fuselage and are used for beam holders mounting, which are installed on pylons and intended for specified cargoes suspension.
- Electrical cargo dropping control system is intended for remote control of dropping of one to four cargoes, which are suspended on a beam holder of BDZ-34 type.
- fault detection of units, parts and components include non-destructive testing, to detect cracks, fractures, surface porosity, nodules, undercuts and unwelded pores by eddy current testing and defects are repaired by welding (utility model patent UA Ne6242, IPC B64F 5/00, publ. 15.04.2005 Bui. No.4).
- a disadvantage of this method is the lack of data on the effectiveness of the repair of certain aircraft systems, such as testing of external suspension installation for small cargo of aircrafts after repair, which results in additional time and economic expenses, in case of installation with undetected damages during fault detection or poor repair.
- the closest to the proposed method is a method for aircraft repair at the aircraft repair plant.
- a method of aviation equipment repair at the aircraft repair company in which the repair process is performed consistently over time in several stages, according to which the first stage consists of acceptance of aviation equipment (AE) to repair, the second phase consists of overall fault detection of AE, which came into repair, the third stage consists of AE dismantling under the approved lists of work according to repair procedure, the fourth stage consists of cleaning and washing of removed parts, components, units and entire object, the fifth stage consists of products grouping with the subsequent transfer to repair, the sixth stage consists of technical diagnostics to determine the technical state of repair objects and methods of the identified faults and defects removal, the seventh stage consists of repairs and design reworking, the eighth stage consists consistently of the AE assembly, installation and development with further transmission of repaired AE to flight-testing station for acceptance tests, the ninth stage consists of ground and flight tests, which together represent acceptance and control tests, the tenth stage consists of AE finishing, painting, preservation, packaging and delivery to
- the utility model is based on the task to ensure repair quality improvement of external suspension installations of aircraft small cargo by entering additional equipment into the diagnosis and repair process with simulated real conditions of operation and loads and to achieve the high level of adaptability and minimize the time and financial expenses to extend service life.
- the specified task in the utility model is achieved due to the fact that the process of aircraft repair as per technical state and modernization is performed consistently over time in several stages, according to which the first stage consists of acceptance of aviation equipment (AE) to repair, the second phase consists of overall AE fault detection, which came to repair, in which data on elements individual service life, products failures and malfunctions identified during the operation and repairs is used, as well as statistical data collected in a database aircraft repair enterprise, to determine the feasibility of any maintenance and repair method of AE components, conduct appropriate adjustment of repair process cycle and deliver data obtained during AE fault detection and appropriately structured, to database of aircraft repair, the third stage consists of AE dismantling for the approved scope of work under repair procedure, whereby during AE dismantling and fault detection of dismountable and non-dismountable equipment only items that require either additional diagnostics or maintenance, or repairs as per stage are disassembles, the fourth stage consists of cleaning and washing of removed parts, components, units and entire object, the fifth stage consists of products grouping with the subsequent transfer to repair, given
- the sixth stage during technical diagnosis to determine the technical state of external suspension installations for small cargo of aircrafts and methods of detected faults and defects removal, uses additional equipment, namely, process test bench for efficiency of external suspension installation for small cargoes, which consists of bearing part of the bench, the pylon with beam holder attached, pneumatic mechanism of cargo simulation with a bracket that is connected to beam holder locks and pressure gauge, the bench can be connected to the network of high air pressure and the voltage source 27 V.
- Figure 1 shows the process test bench for efficiency of external suspension installation for small cargoes - front view
- Fig. 2 shows the process test bench for efficiency of external suspension installation for small cargoes - side view.
- the method of repair as per technical condition of the aircraft is performed consistently over time in several stages, according to which the first stage consists of acceptance of aviation equipment (AE) to repair, the second phase consists of overall fault detection of AE, which came in to repair, in which data is used for elements individual service life, products failures and malfunctions detected during the operation and repairs, as well as statistical data collected in a database of aircraft repair enterprise, to determine the feasibility of any method of maintenance and repair for AE components, conduct appropriate adjustment of repair process cycle and send the data obtained during AE fault detection and appropriately structured to the database of aircraft repair enterprise, the third stage consists of AE dismantling according to the approved scope of work under repair procedure, whereby during AE dismantling and fault detection of dismountable and non-dismountable equipment only those elements that require either additional diagnostics, maintenance or repair as per stage or overhaul are dismantled, the fourth stage consists of cleaning and washing of removed parts, components, units and entire object, the fifth stage consists of products grouping with subsequent transfer to repair, given the fact that the equipment that
- the disassembly works are performed under approved scope of work according to the repair procedure, cleaning, washing and determination of technical state (fault detection] are performed for external suspension installations for small cargos of aircraft. Then repair works are performed under specified damages and instructions for their removal and installation assembly. After the assembly installation is passed to test using the test bench for operational testing of external suspension installation for small cargoes, which allows the holder installation with the pylon to assemblies that simulate the beam holder suspension with the pylon to the aircraft.
- the bench is configured to connect to the air network of high pressure and the voltage source 27 V.
- the bench provides the following:
- the resistance and durability of electrical insulation is performed with the help of megaohmmeter.
- the insulation resistance of electric circuits relative to the housing and between separate electric circuits under normal climatic conditions must be at least 20 MOhm. Electrical insulation must withstand voltage of 500 V, 50 Hz during one minute. Tests are performed by gradually increasing the voltage from zero to 500 V, hold for one minute and gradually decrease back.
- the external suspension installation for small cargo is tested in the following sequence: beam holder is hung with pylon and fixed on the bearing part of the bench.
- Bracket of pneumatic load simulation mechanism is fixed to the beam holder locks and is applied with load force of 500 kgf by compressed air with parameters control by pressure gauge: pressure gauge indicator of 0.392 MPa (0.4 kgf / cm2] corresponds to applied force of 45 kg; 0.882 MPa (0.9 kgf / cm2) - 110 kg; 1,078 MPa (1.1 kgf / cm2) - 150 kg; 1,372 MPa (1.4 kgf / cm2) - 200 kg; 1.862 MPa (1.9 kgf / cm2) - 275 kg; 2,352 MPa (2.4 kgf / cm2] - 370 kg; 3.136 MPa (3.2 kgf / cm2) - 500 kg.
- Operationg testing of the electromechanical actuator of beam holder in "Tactical release” mode and electrical circuits locking is carried out at a voltage of 16V on the remote control unit of beam holder without load simulation under approved scope of work. Operationg testing of the electromechanical actuator of beam holder in "Emergency release” mode and electrical circuits locking is carried out at application of force 500 kg with the help mechanism of cargo simulation of bench under the approved scope of works.
- Patent for invention UA 105281, IPC 2014.01 B64C 35/00, B64C 1/00, B64F 5/00, publ. 25.4.2014 Bull. No.8
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Abstract
The utility model relates to the field of aviation and repair and modernization technology of aircrafts, including the method of diagnosing and repair as per technical state of external suspension installation for small cargoes of aircrafts of 24, 26, 32 types with modifications. The method of repair of the aircraft is performed consistently over time in several stages, according to which the first stage consists of acceptance of aviation equipment (AE) to repair, the second phase consists of overall fault detection of AE, which came in to repair, the third stage consists of AE dismantling for the approved scope of work under repair procedure, the fourth stage consists of cleaning and washing of removed parts, components, units and entire object, the fifth stage consists of products grouping with the subsequent transfer to repair, the sixth stage consists of technical diagnosis to determine the, technical state of repaired objects and methods of detected faults and defects removal using additional equipment, the seventh stage consists of repairs and system reworking, the eighth stage consists of consistent AE assembly, installation and development with the subsequent transfer of the repaired AE to flight-testing station for acceptance tests, the ninth stage consists of ground and flight tests, which together represent acceptance and control tests, new data on failures and defects detected, are organized and sent to the database of aircraft repair enterprise, the tenth stage consists of AE finishing, painting, preservation, packaging and delivery to the customer.
Description
W
METHOD OF EXTERNAL SUSPENSION INSTALLATION DIAGNOSTICS AND REPAIR AS
REQUIRED OF FOR SMALL LOADS
The utility model relates to the field of aviation and aircraft repair and modernization technology, including the method of external suspension diagnosing and repair as per technical state for small loads of aircrafts of 24, 26, 32 types with modifications. Due to significant investments required for new aircraft development or purchases of upgraded, it is important to maintain the existing aviation equipment in operation state and possibility of extending the operational life by repairs as per technical state with upgradeability.
External suspension installation for small loads of aircraft of An-24, 26, 32 types provides suspension of cargoes with 50 to 500 kg weights on the aircraft. Installations contain pylons, beam holders of BDZ-34 type, an electrical cargo dropping control system with beam holders. Pylons are installed outside the fuselage, two on each side in the area of frames Nos. 15-16 and 21-22. Pylons are an intermediate link between the holder and the fuselage and are used for beam holders mounting, which are installed on pylons and intended for specified cargoes suspension. Electrical cargo dropping control system is intended for remote control of dropping of one to four cargoes, which are suspended on a beam holder of BDZ-34 type.
The technology of dismantling, disassembling, further repair and assembling is performed under appropriate process charts.
The most acceptable way of aircraft repair as per technical state and modernization, characterized with assembly and disassembly, fault detection and cleaning with fluid under pressure of chassis, assemblies, parts and components, assembly of the aircraft with the installation of modernized parts and components and acceptance tests with cleaning the units, parts and components by jets of fluid under air absolute pressure for transportation of specified media particles 0.5 ... 0.55 MPa, fault detection of units, parts and components include non-destructive testing, to detect cracks, fractures, surface porosity, nodules, undercuts and unwelded pores by eddy current testing and defects are repaired by welding (utility model patent UA Ne6242, IPC B64F 5/00, publ. 15.04.2005 Bui. No.4).
A disadvantage of this method is the lack of data on the effectiveness of the repair of certain aircraft systems, such as testing of external suspension installation for small cargo of aircrafts after repair, which results in additional time and economic expenses, in case of installation with undetected damages during fault detection or poor repair.
The closest to the proposed method is a method for aircraft repair at the aircraft repair plant. A method of aviation equipment repair at the aircraft repair company, in which the repair process is performed consistently over time in several stages, according to which the first stage consists of acceptance of aviation equipment (AE) to repair, the second phase consists of overall fault detection of AE, which came into repair, the third stage consists of AE dismantling under the approved lists of work according to repair procedure, the fourth stage consists of cleaning and washing of removed parts, components, units and entire object, the fifth stage consists of products grouping with the subsequent transfer to repair, the sixth stage consists of technical diagnostics to determine the technical state of repair objects and methods of the identified faults and defects removal, the seventh stage consists of repairs and design reworking, the eighth stage consists consistently of the AE assembly, installation and development with further transmission of repaired AE to flight-testing station for acceptance tests, the ninth stage consists of ground and flight tests, which together represent acceptance and control tests, the tenth stage consists of AE finishing, painting, preservation, packaging and delivery to the customer, while the second phase of repair consisting of AE fault detection uses data on elements individual service life, failures and malfunctions of products, detected during operation and repairs, as well as statistical data collected in a database of aircraft repair enterprise, to determine the feasibility of any maintenance and repair method for AE components, conduct appropriate adjustment of repair process cycle and send data from the second stage of repair during AE fault detection and appropriately structured, to database of aircraft repair enterprise, at the third stage of repair during AE disassembly and fault detection of dismountable and non- dismountable equipment only those items are dismantled that require either additional diagnostics or maintenance or repair as per stage or overhaul, the fifth stage contains grouping according to adjusted repair process cycle, the equipment, which requires repair as requested or overhaul is transferred to the appropriate areas to perform the seventh stage of repair, the equipment that does not require additional operations, is transferred directly or through intermediate storage in a warehouse, for assembly, installation and development during the eighth stage of repair, new data on failures and defects detected
after the sixth - ninth stages of repair, are organized and sent to the database of aircraft repair enterprise (patent UA 105,281, IPC 2014.01 B64C 35/00, B64C 1/00, B64F 5/00, publ. 25.04.2014 Bull. No.8, ref. to a utility model patent UA 77841, IPC 20134.01 B64C 35/00, B64C 1/00, publ. 25.02.2013 Bull. No.4).
These methods account for the repair work as per technical state, while no data for the repair efficiency of certain aircraft system are available that are associated with the lack of testing of external suspension installations of aircraft small cargo performed after the repair, which leads to additional time and economic expenses in case of their installation with undetected during fault detection damages or poor repair.
The utility model is based on the task to ensure repair quality improvement of external suspension installations of aircraft small cargo by entering additional equipment into the diagnosis and repair process with simulated real conditions of operation and loads and to achieve the high level of adaptability and minimize the time and financial expenses to extend service life.
The specified task in the utility model is achieved due to the fact that the process of aircraft repair as per technical state and modernization is performed consistently over time in several stages, according to which the first stage consists of acceptance of aviation equipment (AE) to repair, the second phase consists of overall AE fault detection, which came to repair, in which data on elements individual service life, products failures and malfunctions identified during the operation and repairs is used, as well as statistical data collected in a database aircraft repair enterprise, to determine the feasibility of any maintenance and repair method of AE components, conduct appropriate adjustment of repair process cycle and deliver data obtained during AE fault detection and appropriately structured, to database of aircraft repair, the third stage consists of AE dismantling for the approved scope of work under repair procedure, whereby during AE dismantling and fault detection of dismountable and non-dismountable equipment only items that require either additional diagnostics or maintenance, or repairs as per stage are disassembles, the fourth stage consists of cleaning and washing of removed parts, components, units and entire object, the fifth stage consists of products grouping with the subsequent transfer to repair, given the fact that the equipment, requiring repair as required or overhaul is transferred to the appropriate area to perform the seventh stage of repair, the equipment that does not require additional operations, is transferred directly or through intermediate storage in a
warehouse, for assembly, installation and development at the eighth stage of repair, the sixth stage consists of technical diagnosis to determine the technical state of repaired objects and methods of detected faults and defects removal using additional equipment, the seventh stage consists of repairs and system reworking, the eighth stage consists of consistent AE assembly, installation and development with the subsequent transfer of the repaired AE to flight-testing station for acceptance tests, the ninth stage consists of ground and flight tests, which together represent acceptance and control tests, new data on failures and defects detected after the sixth - ninth stages of repair, are organized and sent to the database of aircraft repair enterprise, the tenth stage consists of AE finishing, painting, preservation, packaging and delivery to the customer. According to the claimed utility model the sixth stage, during technical diagnosis to determine the technical state of external suspension installations for small cargo of aircrafts and methods of detected faults and defects removal, uses additional equipment, namely, process test bench for efficiency of external suspension installation for small cargoes, which consists of bearing part of the bench, the pylon with beam holder attached, pneumatic mechanism of cargo simulation with a bracket that is connected to beam holder locks and pressure gauge, the bench can be connected to the network of high air pressure and the voltage source 27 V.
The utility model is explained by drawings, in which Figure 1 shows the process test bench for efficiency of external suspension installation for small cargoes - front view, Fig. 2 shows the process test bench for efficiency of external suspension installation for small cargoes - side view.
The following items No marks items of utility model.
1 - beam holder
2 - pylon
3 - bench bearing part
4 - cargo simulation mechanism bracket
5 - cargo simulation pneumatic mechanism
6 - pressure gauge
7 - hose that connects the bench to high pressure
8 - place of beam holder lock
The method of repair as per technical condition of the aircraft is performed consistently over time in several stages, according to which the first stage consists of acceptance of aviation equipment (AE) to repair, the second phase consists of overall fault detection of AE, which came in to repair, in which data is used for elements individual service life, products failures and malfunctions detected during the operation and repairs, as well as statistical data collected in a database of aircraft repair enterprise, to determine the feasibility of any method of maintenance and repair for AE components, conduct appropriate adjustment of repair process cycle and send the data obtained during AE fault detection and appropriately structured to the database of aircraft repair enterprise, the third stage consists of AE dismantling according to the approved scope of work under repair procedure, whereby during AE dismantling and fault detection of dismountable and non-dismountable equipment only those elements that require either additional diagnostics, maintenance or repair as per stage or overhaul are dismantled, the fourth stage consists of cleaning and washing of removed parts, components, units and entire object, the fifth stage consists of products grouping with subsequent transfer to repair, given the fact that the equipment that needs repair as required or overhaul are transmit to the appropriate are to perform the seventh stage of repair, the equipment that does not require additional operations is transferred directly or through intermediate storage in a warehouse, for assembly, installation and development on eighth stage of repair, the sixth stage consists of technical diagnostics to determine the technical state of repair objects and methods detected faults and defects removal, the seventh stage consists of repairs and design reworking, the eighth stage consists of consistent AE assembly, installation and development with subsequent transfer of repaired AE to flight-testing station for acceptance tests, the ninth stage consists of ground and flight tests, which together represent acceptance and control test, the new data on failures and defects detected after the sixth - ninth stage of repair are organized and sent to the database of aircraft repair enterprise, the tenth stage consists of finishing, painting, preservation, packaging and delivery of AE to the customer, during the sixth stage, during technical diagnosis to determine the technical state of external suspension installations for small cargo of aircrafts and methods of detected faults and defects removal, uses additional equipment,
namely, process test bench for efficiency of external suspension installation for small cargoes, which consists of bearing part of the bench, the pylon with beam holder attached, pneumatic mechanism of cargo simulation with a bracket that is connected to beam holder locks and pressure gauge, th bench can be connected to the network of high air pressure and the voltage source 27 V
During the specified method the disassembly works are performed under approved scope of work according to the repair procedure, cleaning, washing and determination of technical state (fault detection] are performed for external suspension installations for small cargos of aircraft. Then repair works are performed under specified damages and instructions for their removal and installation assembly. After the assembly installation is passed to test using the test bench for operational testing of external suspension installation for small cargoes, which allows the holder installation with the pylon to assemblies that simulate the beam holder suspension with the pylon to the aircraft.
The bench is configured to connect to the air network of high pressure and the voltage source 27 V.
The bench provides the following:
- Check the value of insulation resistance of electrical circuits of beam holder at 20 + 50C and relative humidity of 70%;
- Check the insulation of electrical circuits for breakdown and electrical strength at 20 + 50C;
- Operationg testing of the electromechanical actuator of beam holder in the "Tactical and Emergency release" modebi;
- Check the lock of tactical and emergency release circuits.
The resistance and durability of electrical insulation is performed with the help of megaohmmeter. The insulation resistance of electric circuits relative to the housing and between separate electric circuits under normal climatic conditions must be at least 20 MOhm. Electrical insulation must withstand voltage of 500 V, 50 Hz during one minute. Tests are performed by gradually increasing the voltage from zero to 500 V, hold for one minute and gradually decrease back.
The external suspension installation for small cargo is tested in the following sequence: beam holder is hung with pylon and fixed on the bearing part of the bench. Bracket of pneumatic load simulation mechanism is fixed to the beam holder locks and is applied with load force of 500 kgf by compressed air with parameters control by pressure gauge: pressure gauge indicator of 0.392 MPa (0.4 kgf / cm2] corresponds to applied force of 45 kg; 0.882 MPa (0.9 kgf / cm2) - 110 kg; 1,078 MPa (1.1 kgf / cm2) - 150 kg; 1,372 MPa (1.4 kgf / cm2) - 200 kg; 1.862 MPa (1.9 kgf / cm2) - 275 kg; 2,352 MPa (2.4 kgf / cm2] - 370 kg; 3.136 MPa (3.2 kgf / cm2) - 500 kg.
Operationg testing of the electromechanical actuator of beam holder in "Tactical release" mode and electrical circuits locking is carried out at a voltage of 16V on the remote control unit of beam holder without load simulation under approved scope of work. Operationg testing of the electromechanical actuator of beam holder in "Emergency release" mode and electrical circuits locking is carried out at application of force 500 kg with the help mechanism of cargo simulation of bench under the approved scope of works.
Upon the results of operational testing at process bench of external suspension installation efficiency it is transferred to warehouse for further installation on aircraft or additional repair.
Such configuration of utility model ensured the achievement of the task to improve the quality of repair of external suspension installation for small cargoes with simulation of real conditions of operation and loading, a high level of adaptability and minimization of the time and financial expenses to extend the service life.
References sources:
1. Patent for utility model UA Ne6242, IPC B64F 5/00, publ. 15.04.2005 Bull. No. 4
2. Patent for invention UA 105281, IPC 2014.01 B64C 35/00, B64C 1/00, B64F 5/00, publ. 25.4.2014 Bull. No.8
3. Patent for utility model UA 77841, IPC 20134.01 B64C 35/00, B64C 1/00, publ. 25.2.2013 Bull. No.4
Claims
Utility model formula
The method of repair as per technical state of the aircraft is performed consistently over time in several stages, according to which the first stage consists of acceptance of aviation equipment (AE) to repair, the second phase consists of overall fault detection of AE, which came in to repair, in which data of elements individual service life, products failures and malfunctions is used, detected during the operation and repairs, as well as statistical data collected in a database of aircraft repair enterprise, to determine the feasibility of any method of maintenance and repair of AE components, conduct appropriate adjustment of repair process cycle and send the data obtained during AE fault detection and appropriately structured, to database of aircraft repair enterprise, the third stage consists of AE dismantling for the approved scope of work under repair procedure, whereby during AE dismantling and fault detection of dismountable and non-dismountable equipment only items that require either additional diagnostics or maintenance, or repairs as per stage are disassembles, the fourth stage consists of cleaning and washing of removed parts, components, units and entire object, the fifth stage consists of products grouping with the subsequent transfer to repair, given the fact that the equipment, requiring repair as required or overhaul is transferred to the appropriate area to perform the seventh stage of repair, the equipment that does not require additional operations, is transferred directly or through intermediate storage in a warehouse, for assembly, installation and development at the eighth stage of repair, the sixth stage consists of technical diagnosis to determine the technical state of repaired objects and methods of detected faults and defects removal using additional equipment, the seventh stage consists of repairs and system reworking, the eighth stage consists of consistent AE assembly, installation and development with the subsequent transfer of the repaired AE to flight-testing station for acceptance tests, the ninth stage consists of ground and flight tests, which together represent acceptance and control tests, new data on failures and defects detected after the sixth - ninth stages of repair, are organized and sent to the database of aircraft repair enterprise, the tenth stage consists of AE finishing, painting, preservation, packaging and delivery to the customer, at sixth stage during technical diagnosis to determine the technical state of external suspension installations for small cargo of aircrafts and methods of detected faults and defects removal, uses additional equipment, namely, process test bench for efficiency of external suspension installation for small cargoes, which consists of bearing part of the bench, the pylon with beam holder attached, pneumatic mechanism of
cargo simulation with a bracket that is connected to beam holder locks and pressure gauge, the bench can be connected to the network of high air pressure and the voltage source 27 V.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| UAU201603213 | 2016-03-28 | ||
| UAU201603213U UA107634U (en) | 2016-03-28 | 2016-03-28 | METHOD OF DIAGNOSTICS AND REPAIR OF TECHNICAL STATE INSTALLATION OF EXTERNAL SUSPENSION FOR SMALL AIRCRAFT LOADS |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2017171688A1 true WO2017171688A1 (en) | 2017-10-05 |
Family
ID=56561817
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/UA2016/000130 WO2017171688A1 (en) | 2016-03-28 | 2016-11-08 | Method of external suspension installation diagnostics and repair as required of for small loads |
Country Status (2)
| Country | Link |
|---|---|
| UA (1) | UA107634U (en) |
| WO (1) | WO2017171688A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110674585A (en) * | 2019-09-29 | 2020-01-10 | 武汉理工大学 | High-rotating-speed rolling bearing-rotor system local damage fault simulation method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4031364A1 (en) * | 1990-10-04 | 1992-04-09 | Licentia Gmbh | Control data manual entry device for technical systems - has keyboard in plug-in module, alphanumeric display, microcomputer and text ROM |
| UA6242U (en) | 2005-01-17 | 2005-04-15 | Ukrainian Modern Technologies | Method of on-condition repair and modernization of an aircraft |
| US20100073007A1 (en) * | 2004-09-02 | 2010-03-25 | Ziota Technology Inc. | Wireless portable automated harness scanner system and method therefor |
| US20110145026A1 (en) * | 2009-12-10 | 2011-06-16 | Gm Global Technology Operations, Inc. | Software-centric methodology for verification and validation of fault models |
| UA77841U (en) | 2012-09-14 | 2013-02-25 | Товариство З Обмеженою Відповідальністю "Інноваційно-Технологічна Група" | Method for repair of aircraft |
| UA105281C2 (en) | 2012-09-14 | 2014-04-25 | Товариство З Обмеженою Відповідальністю "Нова Інтернаціональна Корпорація" | Method for repair of aviation equipment at repair base |
-
2016
- 2016-03-28 UA UAU201603213U patent/UA107634U/en unknown
- 2016-11-08 WO PCT/UA2016/000130 patent/WO2017171688A1/en active Application Filing
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4031364A1 (en) * | 1990-10-04 | 1992-04-09 | Licentia Gmbh | Control data manual entry device for technical systems - has keyboard in plug-in module, alphanumeric display, microcomputer and text ROM |
| US20100073007A1 (en) * | 2004-09-02 | 2010-03-25 | Ziota Technology Inc. | Wireless portable automated harness scanner system and method therefor |
| UA6242U (en) | 2005-01-17 | 2005-04-15 | Ukrainian Modern Technologies | Method of on-condition repair and modernization of an aircraft |
| US20110145026A1 (en) * | 2009-12-10 | 2011-06-16 | Gm Global Technology Operations, Inc. | Software-centric methodology for verification and validation of fault models |
| UA77841U (en) | 2012-09-14 | 2013-02-25 | Товариство З Обмеженою Відповідальністю "Інноваційно-Технологічна Група" | Method for repair of aircraft |
| UA105281C2 (en) | 2012-09-14 | 2014-04-25 | Товариство З Обмеженою Відповідальністю "Нова Інтернаціональна Корпорація" | Method for repair of aviation equipment at repair base |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110674585A (en) * | 2019-09-29 | 2020-01-10 | 武汉理工大学 | High-rotating-speed rolling bearing-rotor system local damage fault simulation method |
| CN110674585B (en) * | 2019-09-29 | 2021-02-19 | 武汉理工大学 | High-rotating-speed rolling bearing-rotor system local damage fault simulation method |
Also Published As
| Publication number | Publication date |
|---|---|
| UA107634U (en) | 2016-06-10 |
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