CN214748895U

CN214748895U - Modular detects with simulation aircraft device

Info

Publication number: CN214748895U
Application number: CN202121384799.0U
Authority: CN
Inventors: 忻翀华; 董伟亮
Original assignee: Titan Science & Technology Shanghai Co ltd
Current assignee: Titan Science & Technology Shanghai Co ltd
Priority date: 2021-06-22
Filing date: 2021-06-22
Publication date: 2021-11-16
Anticipated expiration: 2031-06-22

Abstract

The utility model provides a modular detects with simulation aircraft device, includes the fuselage, the fuselage includes front-axle beam module, back-axle beam module and longeron module, the rear end fixed connection of front-axle beam module the longeron module, and front-axle beam module and longeron module are on same straight line, the rear end of longeron module is connected perpendicularly the back-axle beam module, and back-axle beam module symmetric arrangement is in the both sides of longeron module, the bottom of front-axle beam module sets up a front wheel group that can turn to, the bilateral symmetry of back-axle beam module sets up two back wheel groups, the rear end of back-axle beam module is fixed to be set up a counter weight support, and this counter weight support is also symmetric arrangement in the both sides of longeron module, be equipped with a plurality of installation positions that are used for placing horizontal balancing weight on the counter weight support, the longeron module is equipped with a standing groove that can be used for placing a plurality of vertical balancing weights on its length direction along. The application provides a modular detects uses simulation aircraft device, simple structure, it is more reasonable to detect the unbalance loading.

Description

Modular detects with simulation aircraft device

Technical Field

The utility model relates to an aircraft tractor detects technical field, concretely relates to modular detects uses simulation aircraft device.

Background

The matched test of the aircraft tractor and various types of airplanes used in civil aircraft places is a necessary condition for whether the aircraft tractor can obtain the traction permission of an aircraft manufacturer, the matched test is used for detecting whether various functions and parameter performances of the aircraft tractor and an airplane assembly with load are in place, the airplane is needed by matched facilities when the aircraft tractor is tested at present, however, the open air test has accident potential, the price of the aircraft test is very high, the types of the airplanes are also many, the risk in the test process is also very high, and the airline company can not provide the airplane for the test.

Application No.: 2016102363278, the name is: the invention relates to a Chinese patent application of an aircraft tractor simulation loading device, which comprises a machine body, wherein a three-point supporting wheel train is arranged at the bottom of the machine body, and a counterweight system is arranged on the machine body; however, because the device is of a symmetrical structure, and the fixed counterweight is poured into the fuselage, the adjustment of the movable counterweight can adjust the weight and the gravity center of the fuselage in a stepped manner, but no matter how the adjustment is carried out, the gravity center is only on the symmetrical middle line of the fuselage, but the gravity center of the aircraft cannot be on the symmetrical middle line of the fuselage in reality, and unbalance loading often exists.

SUMMERY OF THE UTILITY MODEL

In order to solve the problems existing in the prior art, the application provides a modular analog airplane device for detection, which is simple in structure and more reasonable in unbalance loading detection.

In order to realize the technical effect, the utility model discloses a concrete technical scheme as follows:

the utility model provides a modular detects with simulation aircraft device, includes the fuselage, the fuselage includes front-axle beam module, back-axle beam module and longeron module, the rear end fixed connection of front-axle beam module the longeron module, and front-axle beam module and longeron module are on same straight line, the rear end of longeron module is connected perpendicularly the back-axle beam module, and back-axle beam module symmetric arrangement is in the both sides of longeron module, the bottom of front-axle beam module sets up a front wheel group that can turn to, the bilateral symmetry of back-axle beam module sets up two back wheel groups, the rear end of back-axle beam module is fixed to be set up a counter weight support, and this counter weight support is also symmetric arrangement in the both sides of longeron module, be equipped with a plurality of installation positions that are used for placing horizontal balancing weight on the counter weight support, the longeron module is equipped with a standing groove that can be used for placing a plurality of vertical balancing weights on its length direction along.

Further, the longitudinal balancing weight is detachably installed in the placing groove through a bolt.

The working principle of the modular airplane simulating device for detection is as follows:

the proper number of longitudinal counter weights are placed in the placing groove, and the positions for placing are designed, so that the normal load of the airplane can be simulated; on the basis, the transverse balancing weights with the total number and the designed placing positions are placed on the balancing weight support, and the simulation of the unbalance loading of the airplane can be carried out.

When the aircraft tractor needs to be tested, a proper number of longitudinal balancing weights and transverse balancing weights are arranged on the aircraft body, the positions of the balancing weights are adjusted, so that the front wheel set reaches the load required by detection, then the aircraft tractor drives into the lower part of the device, and the simulation test of aircraft traction, namely approaching, clamping, lifting and walking traction (advancing, retreating and steering), is implemented.

According to the technical scheme, compared with the prior art, the utility model, through the quantity of the horizontal balancing weight of adjustment and place the position, can simulate the aircraft unbalance loading and detect, this device can not take place horizontal tilt during the detection, and this detection mode is more reasonable.

Drawings

The present application will be described in further detail below with reference to the accompanying drawings by way of specific embodiments.

FIG. 1 is an overall view of the present invention;

fig. 2 is a top view of the present invention;

FIG. 3 is a schematic side view of the present invention;

wherein, 1, a machine body; 11. a front beam module; 12. a back beam module; 13. a stringer module; 2. a front wheel set; 3. a rear wheel set; 4. a counterweight bracket; 5. a transverse balancing weight; 6. a longitudinal weight block; 7. and (6) placing the groove.

Detailed Description

In order to make the objects, technical solutions and advantages of the present embodiments more clear, the technical solutions in the present embodiments will be described clearly and completely below with reference to the accompanying drawings in the present embodiments, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without any creative effort belong to the protection scope of the present application.

In the description of the present invention, it should be understood that the terms "upper end", "lower end", "tail end", "left and right", "up and down", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for convenience of describing the present application and simplifying the description, but do not indicate or imply that the equipment or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral connections; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

Examples

Referring to fig. 1, 2 and 3, a modular detection aircraft simulation device comprises a body 1, wherein the body 1 comprises a front beam module 11, a back beam module 12 and a longitudinal beam module 13, the back end of the front beam module 11 is fixedly connected with the longitudinal beam module 13, the front beam module 11 and the longitudinal beam module 13 are on the same straight line, the back end of the longitudinal beam module 13 is vertically connected with the back beam module 12, the back beam module 12 is symmetrically arranged on two sides of the longitudinal beam module 13, the bottom end of the front beam module 11 is provided with a front wheel set 2 capable of steering, two back wheel sets 3 are symmetrically arranged on two sides of the back beam module 12, the back end of the back beam module 12 is fixedly provided with a counterweight support 4, the counterweight support 4 is also symmetrically arranged on two sides of the longitudinal beam module 13, the counterweight support 4 is provided with a plurality of mounting positions for placing transverse counterweights 5, the longitudinal beam module 13 is provided with a placing groove 7 capable of placing a plurality of longitudinal counterweights 6 in the length direction thereof .

Wherein, the longitudinal balancing weight is detachably installed in the placing groove through a bolt.

The working principle of the utility model is as follows:

When the aircraft tractor needs to be tested, a proper number of longitudinal balancing weights and transverse balancing weights are arranged on the aircraft body, the positions of the balancing weights are adjusted, so that the front wheel set reaches the load required by detection, then the aircraft tractor drives into the lower portion of the device, and the simulation test of aircraft traction, namely approaching, clamping, lifting and walking traction (advancing, retreating and steering), is implemented.

It is right to have used specific individual example above the utility model discloses expound, only be used for helping to understand the utility model discloses, not be used for the restriction the utility model discloses. To the technical field of the utility model technical personnel, the foundation the utility model discloses an idea can also be made a plurality of simple deductions, warp or replacement.

Claims

1. A modular airplane simulating device for detection is characterized by comprising a machine body, wherein the machine body comprises a front beam module, a rear beam module and a longitudinal beam module, the rear end of the front beam module is fixedly connected with the longitudinal beam module, the front beam module and the longitudinal beam module are on the same straight line, the rear end of the longitudinal beam module is vertically connected with the rear beam module, the back beam modules are symmetrically arranged at the two sides of the longitudinal beam module, the bottom end of the front beam module is provided with a front wheel set capable of steering, two rear wheel sets are symmetrically arranged on two sides of the rear beam module, a counterweight bracket is fixedly arranged at the rear end of the rear beam module, the counterweight brackets are also symmetrically arranged at two sides of the longitudinal beam module, a plurality of mounting positions for placing transverse counterweight blocks are arranged on the counterweight brackets, the longitudinal beam module is provided with a placing groove which can be used for placing a plurality of longitudinal balancing weights along the length direction of the longitudinal beam module.

2. The modular analog aircraft device for detection as claimed in claim 1, wherein said longitudinal weight is removably mounted in said housing slot by means of bolts.