CN106828972B - A kind of aircraft rudder surface drive ram performance testing device - Google Patents
A kind of aircraft rudder surface drive ram performance testing device Download PDFInfo
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- CN106828972B CN106828972B CN201611161899.0A CN201611161899A CN106828972B CN 106828972 B CN106828972 B CN 106828972B CN 201611161899 A CN201611161899 A CN 201611161899A CN 106828972 B CN106828972 B CN 106828972B
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- drive ram
- rudder face
- rocker arm
- rudder
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Abstract
The present invention relates to iron bird Bench Test System, in particular to a kind of aircraft rudder surface drive ram performance testing device.The device includes support, rudder face drive ram [5], rudder face simulating piece [6] and load actuator [7]；The rudder face simulating piece [6] includes rocker arm [6-1,6-3], quality disk [6-2] and shaft [6-4]; rocker arm [6-1,6-3] is fixedly connected with shaft [6-4], and quality disk [6-2] is symmetrically fixed on the both ends shaft [6-4]；Rudder face drive ram [5] one end is fixed by support, the other end is connect by rocker arm [6-1] with rudder face simulating piece [6], load actuator [7] one end is fixed by support, and the other end is connect by rocker arm [6-3] with rudder face simulating piece [6].A kind of aircraft rudder surface drive ram performance testing device is provided, it solves in traditional design, loading system installation is inconvenient, and airborne actuator power output is difficult to measure, the low problem of stiffness simulation dispersion, accuracy, realizes the optimization design to iron bird rack actuator and back segment system.
Description
Technical field
The present invention relates to iron bird Bench Test System, in particular to a kind of aircraft rudder surface drive ram performance test dress
It sets.
Background technique
In iron bird platform development process, actuator and back segment system design and construction often become the main skill that iron bird is developed
Art difficult point.The space layout of actuator and the design of back segment system comprising mechanisms such as stiffness simulation, rudder face simulating piece, loading systems,
The simulation etc. of key parameter, the load of rack are also one of the key technology point that must be taken into consideration.
Several states below the design nothing more than of country's iron bird rack at present, usually trailing edge are rigid rack, machine
It carries actuator front and rear fulcrum and is respectively mounted true airborne support, rudder face also uses true airborne rudder face, maximum in this way
The state of aircraft is simulated, however but high degree improves development cost, while the development process very great Cheng of iron bird rack
It is developed process by structural members such as rudder face and supports on degree to be limited, the at this moment simulation of rudder face aerodynamic loading is usually at rack
The power output of the difficult point of design, airborne actuator is usually unable to measure.Another is exactly actuator and rudder face back segment system half
Simulation table, the rack of this form are usually the support stiffness of actuator front fulcrum support simulation actuator front fulcrum, rigidity mould
The support stiffness of quasi- device simulation actuator rear fulcrum, quality disk simulate rudder face inertia, and loading system uses and airborne actuator pair
The mode on top is generally not used for the iron bird rack arranged according to spatial position, and the usually not torsion between consideration actuator is rigid
Degree.
Summary of the invention
The purpose of the present invention: providing a kind of aircraft rudder surface drive ram performance testing device, solve in traditional design,
Loading system installation is inconvenient, and airborne actuator power output is difficult to measure, the low problem of stiffness simulation dispersion, accuracy, realization pair
The optimization design of iron bird rack actuator and back segment system.
Technical solution of the present invention: a kind of aircraft rudder surface drive ram performance testing device, it is characterized in that: the dress
It sets including support, rudder face drive ram 5, rudder face simulating piece 6 and load actuator 7；
The rudder face simulating piece 6 includes rocker arm 6-1,6-3, quality disk 6-2 and shaft 6-4, rocker arm 6-1,6-3 and shaft
6-4 is fixedly connected, and quality disk 6-2 is symmetrically fixed on the both ends shaft 6-4；
5 one end of rudder face drive ram is fixed by support, and the other end is connect by rocker arm 6-1 with rudder face simulating piece 6, is added
It carries 7 one end of actuator to fix by support, the other end is connect by rocker arm 6-3 with rudder face simulating piece 6.
Preferably, stiffness simulation device 2, the stiffness simulation device packet are provided between support and rudder face drive ram 5
Steel plate 2-1,2-2, supporting element 2-3 are included, is fixed between two panels steel plate by supporting element 2-3.
Preferably, sliding slot 2-4 is provided on steel plate 2-1,2-2, supporting element 2-3 is mounted in sliding slot 2-4.
Preferably, mounting surface of the axis of rudder face drive ram 5 perpendicular to stiffness simulation device 2.
Preferably, force sensor 3, rudder face drive ram are set between stiffness simulation device 2 and rudder face drive ram 5
5 is coaxial with force snesor 3.
Preferably, rocker arm 6-1,6-3 and shaft 6-4 are rigid design.
Preferably, in the work initial position of load actuator 7, rocker arm is vertical with the load axis of actuator 7.
Beneficial effects of the present invention: a kind of aircraft rudder surface drive ram performance testing device of the present invention, according to force-closed
Principle first ensures that actuator and back segment system and iron bird rack stage body form closed system, rudder face loading force is made to be enclosed in peace
It fills inside rack, avoids rudder face loading force to base frame stressing influence, reduce base frame stress, reduce to basic platform
The requirement of frame rigidity, intensity.Rudder face load and installation, simulation rudder face and the unification of excessive rack of actuator consider that collaboration is set
Meter reduces the risk that asynchronous design brings rack to be transformed to the full extent；The design method uses a stiffness simulation device
Simulate the rigidity of back segment system, stiffness simulation device adjustable range is larger, two to three general orders of magnitude, solve iron bird rack with
Airplane design is synchronous to be carried out, and the fixed problem of input parameter is often lacked；Force snesor is installed, it is tired to solve the measurement of actuator power output
Difficult problem；The program is selected simulating piece, both ensure that the key parameter of test, not using simulation rudder face, structural bearings
Under the premise of influencing test effect, development cost has been saved to the maximum extent, and flexible design is easy to implement, and is tried in Aviation Industry
There are very high universal value, and the developing direction of the following iron bird rack back segment system Construction in testing.
Detailed description of the invention
Fig. 1 is structure principle chart of the invention；
Wherein, 1- support, 2- stiffness simulation device, 3- force snesor, 4- support, 5- rudder face drive ram, 6- rudder face mould
Quasi- part, 7- load actuator, 8- support；
Fig. 2 is the structure principle chart of stiffness simulation device；
Wherein, 2-1 steel plate, 2-2 steel plate, 2-3 supporting element, 2-4 sliding slot, 2-5 cover board, 2-6 cover board；
Fig. 3 is the structure principle chart of rudder face simulating piece；
Wherein, 6-1 rocker arm, 6-2 mass disk, 6-3 rocker arm, 6-4 shaft.
Specific embodiment
Present invention is further described in detail with reference to the accompanying drawings of the specification, please refers to Fig. 1, Fig. 2, Fig. 3.
The device includes support, rudder face drive ram 5, rudder face simulating piece 6 and load actuator as shown in Figure 1:
7；The rudder face simulating piece 6 includes rocker arm 6-1,6-3, quality disk 6-2 and shaft 6-4, and rocker arm 6-1,6-3 and shaft 6-4 are solid
Fixed connection, quality disk 6-2 are symmetrically fixed on the both ends shaft 6-4；5 one end of rudder face drive ram is fixed by support, the other end
Connect by rocker arm 6-1 with rudder face simulating piece 6, load 7 one end of actuator fixed by support, the other end by rocker arm 6-3 with
Rudder face simulating piece 6 connects.
Aircraft rudder surface drive ram performance testing device comprising the forward and backward Support rigidity simulation of actuator and should at least be made
Torsion stiffness simulation between dynamic device, the simulation of rudder face rotary inertia, rudder face loading device, i.e. simulation rudder face aerodynamic loading.This
The test device that invention provides covers the above content.
Rigidity comprehensive simulation used passes through stiffness simulation device and realizes.As shown in Fig. 2, stiffness simulation device 2 is by steel plate 2-1,
2-2, cover board 2-5,2-6, supporting element 2-3 composition.When design, the forward and backward fulcrum support rigidity of rudder face drive ram, actuator connect
The torsion stiffness connect between rudder face is converted onto stiffness simulation device 2, realizes the comprehensive simulation to this section of rigidity.Therefore, rudder face
The devices other parts such as simulating piece, support do not need to simulate rigidity, design by rigid body, i.e., rigidity is stiffness simulation
3~5 times of device rigidity, supporting element 2-3 do not have the strict demand of structure type, realize stiffness tuning.
It is equipped with sliding slot 2-4, slide up and down supporting element 2-3 can 2-4 along the chute, to realize rigidity in steel plate 2-1,2-2
Adjust, therefore, the rigidity value that stiffness simulation device 2 is simulated is adjustable, and stiffness simulation device adjustable range is larger, it is general it is adjustable two to three
The order of magnitude solves test-bed progress synchronous with airplane design, often lacks the fixed problem of input parameter.In steel plate 2-1, the side 2-2
Face is equipped with scale value corresponding with rigidity (determining by demarcating), the quick adjusting of the position part 2-3 is used to support, when adjusting is arrived
After accurate location, supporting element 2-3 is by bolt and cover board 2-5,2-6 connection, it is made to be fixed on steel plate 2-1, on 2-2.
The installation point of stiffness simulation device 2 and support 1 and force snesor 3 is located at the center of steel plate 2-1,2-2, same with actuator
Axis.
Experimentation cost can be reduced using rudder face simulating piece, be easy to implement rack construction and aircraft Synchronization Design.Such as Fig. 3 institute
Show, the rudder face simulating piece 6 includes rocker arm 6-1,6-3, quality disk 6-2 and shaft 6-4, and rocker arm 6-1,6-3 and shaft 6-4 are solid
Fixed connection, quality disk 6-2 are fixed on the side shaft 6-4 or are arranged symmetrically.Rocker arm 6-1,6-3, shaft 6-4 press rigid body design.
Rudder face simulating piece need to simulate rudder face rotary inertia, for this purpose, quality disk 6-2 quantity is adjustable, quality disk is adjustable inertia mould
Intend adjustable range 10%~20%, quality disk mass block 6-5 can carry out the fine tuning of inertia, it is ensured that the standard of rudder face rotary inertia
Really simulation.When neutral position, 6 upper rocker arm 6-1 center line of rudder face simulating piece is vertical with 5 axis of rudder face drive ram；It shakes thereon
Arm 6-3 center line is vertical with load actuator axis.
For simulating rudder face aerodynamic loading, guarantee is consistent with the output torque that load actuator requires to be load actuator 7
It can.As shown in Figure 1, load actuator axis keeps horizontal when neutral position.Described device and the part test rack, which are formed, to be sealed
Structure is closed, when loading rudder face, loading force can be closed in this structure, reduce rigidity, intensity requirement to support stand.
As shown in Figure 1, support 1 is stiffness simulation device erection support, with stiffness simulation device by flanged joint, when designing
It is designed by by rigid body.1 end face of support is it is ensured that stiffness simulation device mounting surface and force snesor 3, support 4, rudder face driving are made
Dynamic 5 axis of device is vertical.
As shown in Figure 1, force snesor 3 is between stiffness simulation device 2 and rudder face drive ram 5, for measuring rudder face
Actuator power output, force snesor 3 use flanged joint.Support 4 is rudder face drive ram erection support, by pressing when design
Rigid body is designed.
Rudder face drive ram 5 is consistent with airborne part.One end is connected by support 4 and force snesor 3 and stiffness simulation device 2
It connects, the other end is connect by rocker arm 6-1 with rudder face simulating piece 6.Support 8 is load actuator erection support, by rigid when designing
Body is designed.
The component and the section transitions rack form force-closed system, and the supporting table of bridging table is carried out according to this principle
Body design.2 center line of stiffness simulation device, 3 axis of force snesor, 4 axis of support and 5 axis of rudder face drive ram keep same
Axis.
Claims (7)
1. a kind of aircraft rudder surface drive ram performance testing device, it is characterized in that: the device includes support, rudder face driving
Actuator (5), rudder face simulating piece (6) and load actuator (7)；
The rudder face simulating piece (6) includes the first rocker arm (6-1), the second rocker arm (6-3), quality disk (6-2) and shaft (6-
4), the first rocker arm (6-1), the second rocker arm (6-3) are fixedly connected with shaft (6-4), and quality disk (6-2) is symmetrically fixed on shaft
The both ends (6-4)；
Rudder face drive ram (5) one end is fixed by support, and the other end passes through the first rocker arm (6-1) and rudder face simulating piece (6)
Connection, load actuator (7) one end are fixed by support, and the other end is connected by the second rocker arm (6-3) and rudder face simulating piece (6)
It connects.
2. a kind of aircraft rudder surface drive ram performance testing device according to claim 1, it is characterized in that: support and rudder
It is provided between face drive ram (5) stiffness simulation device (2), the stiffness simulation device includes steel plate (2-1,2-2), support
Part (2-3), it is fixed by supporting element (2-3) between two panels steel plate.
3. a kind of aircraft rudder surface drive ram performance testing device according to claim 2, it is characterized in that: steel plate (2-
1,2-2) it is provided on sliding slot (2-4), supporting element (2-3) is mounted in sliding slot (2-4).
4. a kind of aircraft rudder surface drive ram performance testing device according to claim 2, it is characterized in that: rudder face driving
Mounting surface of the axis of actuator (5) perpendicular to stiffness simulation device (2).
5. a kind of aircraft rudder surface drive ram performance testing device according to claim 2, it is characterized in that: stiffness simulation
Force sensor (3) are set between device (2) and rudder face drive ram (5), rudder face drive ram (5) and force snesor (3)
Coaxially.
6. a kind of aircraft rudder surface drive ram performance testing device according to claim 1, it is characterized in that: the first rocker arm
(6-1), the second rocker arm (6-3) and shaft (6-4) are rigid design.
7. a kind of aircraft rudder surface drive ram performance testing device according to claim 1, it is characterized in that: make in load
The work initial position of dynamic device (7), rocker arm are vertical with the load axis of actuator (7).
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| CN201611161899.0A CN106828972B (en) | 2016-12-15 | 2016-12-15 | A kind of aircraft rudder surface drive ram performance testing device |
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| CN201611161899.0A CN106828972B (en) | 2016-12-15 | 2016-12-15 | A kind of aircraft rudder surface drive ram performance testing device |
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| CN106828972B true CN106828972B (en) | 2019-03-19 |
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| CN108051199B (en) * | 2018-02-09 | 2019-07-05 | 西北工业大学 | Rocker-arm test stand for performance of linear electromechanical actuator |
| CN109470384B (en) * | 2018-11-08 | 2020-09-18 | 北京精密机电控制设备研究所 | Output force measuring and calibrating device of double-path brake actuator |
| CN109635389B (en) * | 2018-11-29 | 2022-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Rigidity test data processing method for electric steering engine |
| CN111003208A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Nonlinear force loading test device for airplane speed reduction plate |
| CN111159826B (en) * | 2019-12-25 | 2023-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Method and equipment for optimizing fulcrum positions of multi-fulcrum airfoil structure |
| CN112362370B (en) * | 2020-10-19 | 2023-02-03 | 中国运载火箭技术研究院 | Simple steering engine load testing device |
| CN113237746B (en) * | 2020-12-29 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Control surface operation test bed and iron bird bed control surface simulation device strength analysis method |
| CN112965455B (en) * | 2020-12-29 | 2022-10-11 | 中国航空工业集团公司西安飞机设计研究所 | Device and method for testing dynamic characteristics of actuator |
| CN114476120A (en) * | 2021-12-31 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Test platform for airplane front-end power-assisted mechanical control system |
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