CN110963074B - Unmanned aerial vehicle undercarriage signal simulation system - Google Patents
Unmanned aerial vehicle undercarriage signal simulation system Download PDFInfo
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- CN110963074B CN110963074B CN201911361021.5A CN201911361021A CN110963074B CN 110963074 B CN110963074 B CN 110963074B CN 201911361021 A CN201911361021 A CN 201911361021A CN 110963074 B CN110963074 B CN 110963074B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention belongs to the technical field of airborne system test devices, and particularly relates to an unmanned aerial vehicle undercarriage signal simulation system; the simulation system consists of a control display unit, a wheel-mounted switch unit, a wheel-mounted signal interface unit, an undercarriage in-place switch unit and an undercarriage in-place signal interface unit; three internal switches are arranged in the wheel-mounted switch unit and are in a grounding or suspension state under the control of the control display unit; the wheel-borne signal interface unit is provided with wheel-borne signal interfaces corresponding to three internal switches in the wheel-borne switch unit; three internal switches are arranged in the landing gear in-place switch unit and are in a grounding or suspending state under the control of the control display unit; the landing gear in-place signal interface unit is provided with landing gear in-place signal interfaces corresponding to three internal switches in the landing gear in-place switch unit; the device provided by the invention has a simple structure and is convenient to use and operate; can be used independently or integrally.
Description
Technical Field
The invention belongs to the technical field of airborne system test devices, and particularly relates to an unmanned aerial vehicle undercarriage signal simulation system; the device is used for simulating the landing gear state signal required in the ground test work of the unmanned aerial vehicle.
Background
The landing gear signals mainly comprise wheel loads and landing gear in-place, and are discrete quantity system signals which have great influence on the work of each system of the airplane; the landing gear signals include nose gear, left main gear, and right main gear signals. The wheel-mounted signals have two states of 'air' and 'ground', and the landing gear receiving in-place signals have two states of 'in-place' and 'not in-place'. The landing gear signal directly participates in the calculation of an aircraft system and influences the working state of the system on the aircraft. In the production and manufacture of an airplane, a plurality of onboard system ground test works need to provide certain landing gear state signals, such as: and performing system tests on airplane front wheel control, braking, flying pipes, tasks and the like.
At present, the landing gear state signals of ground test on a large number of aircraft systems of unmanned aerial vehicles are all generally adopted to directly receive and release the landing gear, or are realized by tools such as gong and cutter through mechanical force change wheel-mounted switch state, and the like, so that the system mainly has the defects of poor working harmony, easy damage influence on the system, many requirements of matching personnel, poor working efficiency, and especially some special task system test works, and great examination is brought to safety protection work and the like.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides an unmanned aerial vehicle undercarriage signal simulation system, which aims to solve the problems that in the ground test process, the undercarriage state signal acquisition work is complicated, multi-party coordination is needed, and potential safety hazards exist.
The technical scheme is as follows: the invention provides an unmanned aerial vehicle undercarriage signal simulation system which mainly comprises a control display unit (1), a wheel-mounted switch unit (2), a wheel-mounted signal interface unit (3), an undercarriage in-place switch unit (4), an undercarriage in-place signal interface unit (5), a wheel-mounted signal cable (6), an undercarriage in-place signal cable (7) and the like, wherein the wheel-mounted signal interface unit (3) and the undercarriage in-place signal interface unit (5) are respectively connected to a corresponding system on a plane through the wheel-mounted signal cable (6) and the undercarriage in-place signal cable (7) instead of an onboard wheel-mounted switch electrical interface and an undercarriage in-place signal switch electrical interface, so that the undercarriage state signal output simulation required for the work of onboard ground tests and the like is provided.
The invention relates to an unmanned aerial vehicle undercarriage signal simulation system, which mainly comprises the following technical methods:
1. the control ports 'a', 'B' and 'C' of the control display unit (1) control the internal switches 'K1', 'K2' and 'K3' of the wheel-mounted switch unit (2), so that the front wheel-mounted signal 'A', the left main wheel-mounted signal 'B' and the right main wheel-mounted signal 'C' of the wheel-mounted signal interface unit (3) which are connected with the output of the wheel-mounted switch unit (2) are respectively in a grounding or suspending state, and the simulation of the states of 'air' and 'ground' of the wheel-mounted signals of the airplane is realized;
2. internal switches K4, K5 and K6 of the landing gear in-place switch unit (4) are controlled through control ports D, E and F of the control display unit (1), so that a nose landing gear in-place signal D, a left main landing gear in-place signal E and a right main landing gear in-place signal F of the landing gear in-place signal interface unit (5) output and connected by the landing gear in-place switch unit (4) are in a grounded or suspended state respectively, and the in-place and in-place state simulation of the landing gear of the airplane is realized.
Preferably, a first internal switch, a second internal switch and a third internal switch are arranged in the wheel-mounted switch unit (2) and are respectively connected with a front wheel-mounted signal interface A, a left main wheel-mounted signal interface B and a right main wheel-mounted signal interface C in the wheel-mounted signal interface unit (3) through a wheel-mounted signal cable (6); the undercarriage signal simulation system is connected with an onboard system through a wheel-mounted signal interface unit (3) to ensure that the undercarriage signal simulation system can provide required wheel-mounted simulation signal output for an airplane ground test.
Preferably, a fourth internal switch, a fifth internal switch and a sixth internal switch are arranged in the undercarriage in-place switch unit (4) and are respectively connected with a front undercarriage in-place signal D interface, a left main undercarriage in-place signal E interface and a right main undercarriage in-place signal F interface in the undercarriage in-place interface unit (5) through an undercarriage in-place signal cable (7); the landing gear signal simulation system can provide the required landing gear in-place simulation signal output for the airplane ground test.
Preferably, the control display unit (1) controls the wheel-mounted switch unit (2) and the undercarriage in-place switch unit (4) independently without interfering with each other; the reliability of analog signal control output is ensured.
Preferably, the control display unit (1) comprises a control software module for providing an operation and state display environment for the control output of the wheel-borne analog signal and the landing gear in-place analog signal of the unmanned aerial vehicle landing gear signal simulation system.
Preferably, the control display unit (1), the wheel-mounted switch unit (2), the landing gear in-place switch unit (4) and the like all adopt circuit devices with micro power consumption, and through integrated design, a portable and small portable device can be realized, and the portable device can be conveniently used and operated in various outfield special environments.
The beneficial technical effects are as follows: the unmanned aerial vehicle undercarriage signal simulation system provided by the invention is simple in structure and convenient to use and operate. The device can be used as an independent device, and can also be integrated into other equipment systems to realize corresponding functions, so that the working efficiency is improved, and the safety risk is reduced. The effect of greatly improving the working efficiency is remarkable, and the application and popularization value is huge.
Drawings
FIG. 1: the invention relates to a circuit schematic block diagram of an unmanned aerial vehicle undercarriage signal simulation system;
in fig. 1: 1-controlling a display unit; 2-a wheel-mounted switch unit; 3-a wheel-mounted signal interface unit; 4-landing gear in-place switch unit; 5-landing gear in-place signal interface unit; 6-a wheel-mounted signal cable; landing gear in-place signal cable 7.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
1. An unmanned aerial vehicle undercarriage signal simulation system is mainly formed by circuit system unit design, wherein the circuit system unit design comprises a control display unit (1), a wheel-mounted switch unit (2), a wheel-mounted signal interface unit (3), an undercarriage in-place switch unit (4), an undercarriage in-place signal interface unit (5), a wheel-mounted signal cable (6), an undercarriage in-place signal cable (7) and the like.
2. As shown in fig. 1, the technical principle implementation method of the unmanned aerial vehicle undercarriage signal simulation system is as follows:
the control ports 'a', 'B' and 'C' of the control display unit (1) control internal switches 'K1', 'K2' and 'K3' of the wheel-mounted switch unit (2), so that a front wheel-mounted signal 'A', a left main wheel-mounted signal 'B' and a right main wheel-mounted signal 'C' of the wheel-mounted signal interface unit (3) which are connected with the wheel-mounted switch unit (2) are respectively in a grounded state or a suspended state, and simulation of air and ground state signals of airplane wheel-mounted signals can be achieved; internal switches K4, K5 and K6 of the landing gear in-place switch unit (4) are controlled through control ports D, E and F of the control display unit (1), so that a nose landing gear in-place signal D, a left main landing gear in-place signal E and a right main landing gear in-place signal F of the landing gear in-place signal interface unit (5) output and connected by the landing gear in-place switch unit (4) are in a grounded or suspended state respectively, and simulation of state signals of in-place and not in-place of the landing gear of the airplane can be achieved.
In the specific implementation process, can pass through unmanned aerial vehicle undercarriage signal analog system's wheel carries signal cable (6) and undercarriage signal cable (7) that targets in place replace on-board wheel year switch cable interface and undercarriage signal cable interface that targets in place (5) respectively with wheel year signal interface unit (3) and undercarriage signal interface that targets in place (5) and be connected with the corresponding system on the aircraft, the corresponding real object system on the substitute aircraft that can be very convenient provides required undercarriage switch analog signal output such as ground test work, thereby work efficiency such as ground test is improved, personnel's demand is reduced, labor intensity, reduce unexpected damage risk and personnel's safety risk that bring aircraft system.
In the specific implementation process, control hardware channels of the control display unit (1) for the wheel-mounted switch unit (2) and the undercarriage-in-place switch unit (4) are mutually independent and do not interfere with each other, but the logical relationship between the wheel-mounted analog signal and the undercarriage-in-place analog signal output is ensured to be (1) when the wheel-mounted signal is in a ground state, the undercarriage-in-place signal is in a non-in-place-on-receiving state; (2) when the landing gear in-place signal is in the 'receiving up in place' state, the wheel load signal is in the 'air' state.
In the specific implementation process of the unmanned aerial vehicle undercarriage signal simulation system, when internal switches K1, K2 and K3 of a wheel-mounted switch unit (2) are controlled by a control display unit (1) and are in a suspended state, a wheel-mounted signal interface unit (3) sends an unmanned aerial vehicle undercarriage 'air' state simulation signal, and otherwise, sends an unmanned aerial vehicle undercarriage 'ground' state simulation signal; correspondingly, when the fourth internal switch, the fifth internal switch and the sixth internal switch are all in a suspended state under the control of the control display unit, the landing gear in-place signal interface unit (5) sends an in-place signal of landing gear take-up, otherwise, the landing gear is not in place.
On the basis of the design of the unmanned aerial vehicle undercarriage signal simulation system, the control display unit (1) comprises a control software module and a liquid crystal display screen so as to provide an interface environment for system operation control and observation.
The above control process may be performed by control instructions stored in a computer-readable storage medium, which when executed, are used to implement the above simulation control method. The method is implemented by adopting computer control instructions, so that errors in the manual operation process can be effectively prevented.
The above-mentioned method related to the circuit unit structure and the connection relationship only embody the preferred technical solution of the present invention, and the changes that may be made to some parts of the method by those skilled in the art all embody the principle of the present invention, and belong to the protection scope of the present invention.
Claims (10)
1. Unmanned aerial vehicle undercarriage signal simulation system, its characterized in that: the simulation system consists of a control display unit (1), a wheel-mounted switch unit (2), a wheel-mounted signal interface unit (3), an undercarriage in-place switch unit (4), an undercarriage in-place signal interface unit (5), a wheel-mounted signal cable (6) and an undercarriage in-place signal cable (7); a first internal switch, a second internal switch and a third internal switch are arranged in the wheel-mounted switch unit (2), and the three internal switches are in a grounding or suspension state under the control of the control display unit (1); the wheel-mounted signal interface unit (3) is provided with a front wheel-mounted signal interface A, a left main wheel-mounted signal interface B and a right main wheel-mounted signal interface C which correspond to three internal switches in the wheel-mounted switch unit (2); a fourth internal switch, a fifth internal switch and a sixth internal switch are arranged in the landing gear in-place switch unit (4), and the three internal switches are in a grounding or suspending state under the control of the control display unit (1); the landing gear in-place signal interface unit (5) is provided with a front landing gear in-place receiving signal D interface, a left main landing gear in-place receiving signal E interface and a right main landing gear in-place receiving signal F interface which correspond to three internal switches in the landing gear in-place switch unit (4); the wheel-mounted switch unit (2) is connected with the wheel-mounted signal interface unit (3) through a wheel-mounted signal cable (6), and the undercarriage in-place switch unit (4) is connected with the undercarriage in-place signal interface unit (5) through an undercarriage in-place signal cable (7); and output simulation of the wheel load signal and the landing gear in-place signal is realized.
2. The unmanned aerial vehicle landing gear signal simulation system of claim 1, wherein: when a first internal switch, a second internal switch and a third internal switch of the wheel-mounted switch unit (2) are all in a suspended state under the control of the control display unit (1), the wheel-mounted signal interface unit (3) sends an 'air' state signal, otherwise, a 'ground' state signal is sent.
3. An unmanned aerial vehicle landing gear signal simulation system according to claim 1 or 2, wherein: a first internal switch, a second internal switch and a third internal switch are arranged in the wheel-mounted switch unit (2) and are respectively connected with a front wheel-mounted signal interface A, a left main wheel-mounted signal interface B and a right main wheel-mounted signal interface C in the wheel-mounted signal interface unit (3) through wheel-mounted signal cables (6).
4. The unmanned aerial vehicle landing gear signal simulation system of claim 1, wherein: when the fourth internal switch, the fifth internal switch and the sixth internal switch are all in a suspended state under the control of the control display unit, the landing gear in-place signal interface unit sends out a landing gear in-place state signal, and otherwise, the landing gear in-place signal interface unit sends out an in-place state signal.
5. An unmanned aerial vehicle landing gear signal simulation system according to claim 1 or 4, wherein: a fourth internal switch, a fifth internal switch and a sixth internal switch are arranged in the undercarriage in-place switch unit (4) and are respectively connected with a front undercarriage in-place signal interface D, a left main undercarriage in-place signal interface E and a right main undercarriage in-place signal interface F in the undercarriage in-place signal interface unit (5) through an undercarriage in-place signal cable (7).
6. The unmanned aerial vehicle landing gear signal simulation system of claim 1, wherein: when the simulation system is used, the onboard wheel-mounted switch cable and the undercarriage in-place signal cable are respectively replaced by the onboard wheel-mounted signal cable (6) and the undercarriage in-place signal cable (7) to be connected with the corresponding onboard system.
7. The unmanned aerial vehicle landing gear signal simulation system of claim 1, wherein: the control display unit (1), the wheel-mounted switch unit (2) and the landing gear in-place switch unit (4) are all designed by circuit device integration with micro power consumption.
8. The unmanned aerial vehicle landing gear signal simulation system of claim 1, wherein: the control display unit (1) controls the wheel-mounted switch unit and the landing gear in-place switch unit independently without interfering with each other.
9. An unmanned aerial vehicle landing gear signal simulation system according to claim 1 or 8, wherein: the control display unit (1) is provided with a liquid crystal display and a computer-readable storage medium.
10. The unmanned aerial vehicle landing gear signal simulation system of claim 9, wherein: the computer-readable storage medium stores computer-executable instructions that, when executed, implement control of a wheel-mounted switch unit (2) and a landing gear-in-place switch unit (4).
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| CN201911361021.5A CN110963074B (en) | 2019-12-25 | 2019-12-25 | Unmanned aerial vehicle undercarriage signal simulation system |
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| CN201911361021.5A CN110963074B (en) | 2019-12-25 | 2019-12-25 | Unmanned aerial vehicle undercarriage signal simulation system |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6353793B1 (en) * | 1999-02-01 | 2002-03-05 | Aero Modifications & Consulting, Llc | System and apparatus for determining the center of gravity of an aircraft |
| CN102968059A (en) * | 2012-08-10 | 2013-03-13 | 中国商用飞机有限责任公司 | Aircraft landing gear simulator |
| CN203101944U (en) * | 2012-12-21 | 2013-07-31 | 四川华星测试技术研究所 | Measurement and control system for iron-bird experiment table for energy section and undercarriage section |
| CN203422664U (en) * | 2013-09-22 | 2014-02-05 | 四川海特高新技术股份有限公司 | Undercarriage control and interface assembly testboard |
| CN204440710U (en) * | 2015-01-07 | 2015-07-01 | 哈尔滨飞机工业集团有限责任公司 | A kind of undercarriage simulation folding and unfolding control circuit |
| CN105291936A (en) * | 2015-11-23 | 2016-02-03 | 中国航天空气动力技术研究院 | Ground integrated test apparatus for UAV (unmanned aerial vehicle) undercarriages |
| CN105511306A (en) * | 2015-11-26 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane function test console |
| CN106742048A (en) * | 2016-11-18 | 2017-05-31 | 中航飞机起落架有限责任公司 | A kind of Aircraft landing gear system RS422 bus datas verification method and device |
| CN108106856A (en) * | 2016-11-24 | 2018-06-01 | 中航贵州飞机有限责任公司 | A kind of airplane brake system tests and analyzes device |
| CN208459789U (en) * | 2017-11-06 | 2019-02-01 | 中航通飞华南飞机工业有限公司 | A kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0314760D0 (en) * | 2003-06-25 | 2003-07-30 | Westland Helicopters | Display system |
| GB0517351D0 (en) * | 2005-08-24 | 2005-10-05 | Airbus Uk Ltd | Landing load monitor for aircraft landing gear |
| CN203601583U (en) * | 2013-11-29 | 2014-05-21 | 浙江省计量科学研究院 | System for testing performance of airplane porthole assembly |
| CN206243509U (en) * | 2016-11-17 | 2017-06-13 | 成都飞机工业（集团）有限责任公司 | A kind of analogue means of aircraft test signal |
| US10502760B2 (en) * | 2017-04-11 | 2019-12-10 | General Electric Company | Pitot-static air data test system with pilot and co-pilot verification |
| CA2971890A1 (en) * | 2017-06-22 | 2018-12-22 | Bell Helicopter Textron Inc. | System and method for performing a test procedure |
| CN208746274U (en) * | 2018-08-01 | 2019-04-16 | 成都飞机工业（集团）有限责任公司 | A kind of Portable aircraft wheel load simulator |
| CN209496282U (en) * | 2019-03-21 | 2019-10-15 | 成都凯天电子股份有限公司 | The device of integration test unmanned plane undercarriage control controller |
-
2019
- 2019-12-25 CN CN201911361021.5A patent/CN110963074B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6353793B1 (en) * | 1999-02-01 | 2002-03-05 | Aero Modifications & Consulting, Llc | System and apparatus for determining the center of gravity of an aircraft |
| CN102968059A (en) * | 2012-08-10 | 2013-03-13 | 中国商用飞机有限责任公司 | Aircraft landing gear simulator |
| CN203101944U (en) * | 2012-12-21 | 2013-07-31 | 四川华星测试技术研究所 | Measurement and control system for iron-bird experiment table for energy section and undercarriage section |
| CN203422664U (en) * | 2013-09-22 | 2014-02-05 | 四川海特高新技术股份有限公司 | Undercarriage control and interface assembly testboard |
| CN204440710U (en) * | 2015-01-07 | 2015-07-01 | 哈尔滨飞机工业集团有限责任公司 | A kind of undercarriage simulation folding and unfolding control circuit |
| CN105291936A (en) * | 2015-11-23 | 2016-02-03 | 中国航天空气动力技术研究院 | Ground integrated test apparatus for UAV (unmanned aerial vehicle) undercarriages |
| CN105511306A (en) * | 2015-11-26 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane function test console |
| CN106742048A (en) * | 2016-11-18 | 2017-05-31 | 中航飞机起落架有限责任公司 | A kind of Aircraft landing gear system RS422 bus datas verification method and device |
| CN108106856A (en) * | 2016-11-24 | 2018-06-01 | 中航贵州飞机有限责任公司 | A kind of airplane brake system tests and analyzes device |
| CN208459789U (en) * | 2017-11-06 | 2019-02-01 | 中航通飞华南飞机工业有限公司 | A kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size |
Non-Patent Citations (1)
| Title |
|---|
| 某型飞机起落架收放过程仿真;张强等;《流体传动与控制》;20090315(第02期);全文 * |
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