Tandem helicopter cabin pedal static strength test loading device

Abstract

The utility model belongs to the technical field of helicopter control system strength tests, and particularly relates to a tandem helicopter cabin pedal static strength test loading device. Comprising a fixed floor, a pedal loading claw, a sensor, a sensor connecting rod, an elastic thread sleeve, a loading lug connecting rod, a mounting lug, a loading stand column and a floor cross beam, the fixed floor is mounted on a cockpit floor; the floor beam is installed on a fixed floor, and the two loading stand columns are installed at the two ends of the floor beam and stand on the fixed floor. A mounting lug is fixed on each of the two loading upright posts; the mounting lugs are hinged with the loading lug connecting rods; the other end of the elastic screw sleeve is connected with the sensor connecting rod; the sensor connecting rod is connected with one end of the sensor, and the other end is connected with the pedal loading claw. And the pedal loading claw is contacted and fastened with the pedal supporting rod.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of helicopter control system strength test, especially relates to a longitudinal type helicopter cabin footrest static strength test loading device. BACKGROUND

[0002] The helicopter footrest is a key component of the helicopter, and must meet the strength requirements of the structure and the reasonable stiffness characteristics in design. The helicopter footrest static strength test is mainly used for verifying whether the static strength of the helicopter footrest structure and the body support structure meets the design requirements, and providing necessary data for verifying the static strength calculation method and the structure rationality. The main test content of the helicopter footrest static strength test is that the footrest rod is first locked in the neutral position, and then loaded in the direction perpendicular to the footrest. The longitudinal type helicopter cabin space is narrow, and the loading space is more limited. Moreover, the footrest deforms greatly during the test, and it is very difficult to carry out the test. It is difficult to normally carry out the loading, the fuselage skin needs to be damaged, and the angle control of the loading is difficult. UTILITY MODEL CONTENT

[0003] The utility model discloses a longitudinal type helicopter cabin footrest static strength test loading device, which solves the above problems.

[0004] TECHNICAL SCHEME

[0005] A longitudinal type helicopter cabin footrest static strength test loading device, comprising: a fixed floor, a footrest loading claw, a sensor, a sensor connecting rod, a loose sleeve, a loading ear connecting rod, a mounting ear, a loading column and a floor crossbeam.

[0006] The fixed floor is installed on the cockpit floor.

[0007] The floor crossbeam is installed on the fixed floor, and two loading columns are installed at the two ends of the floor crossbeam and stand on the fixed floor.

[0008] One mounting ear is fixed on each of the two loading columns, and the mounting ear is hinged with the loading ear connecting rod.

[0009] One end of the loose sleeve is connected with the loading ear connecting rod, and the other end is connected with the sensor connecting rod.

[0010] One end of the sensor connecting rod is connected with the sensor, and the other end of the sensor is connected with the footrest loading claw.

[0011] The footrest loading claw is in contact with the footrest support rod and is buckled tightly.

[0012] Further, the fixed floor is fixed with the cockpit floor through a countersunk hole.

[0013] Further, the structure further comprises two floor longitudinal beams and two support inclined rods.

[0014] Two floor longitudinal beams are installed on the fixed floor and are perpendicular to the floor cross beam and close to the floor cross beam;

[0015] Two support inclined rods are connected to the end of the floor longitudinal beam away from the end of the floor cross beam, and the other end is connected to the middle of the loading column.

[0016] Further, the loading column is a U-shaped beam, and a plurality of mounting holes are arranged on the upper portion of the U-shaped beam for adjusting the angle of the mounting lug.

[0017] Further, the semicircular loading end of the pedal loading claw is buckled to the pedal support rod, and the threaded joint end of the pedal loading claw is connected with the sensor.

[0018] Further, the two ends of the loose nut are threaded segments, and the pedal support rod is loaded by rotating the loose nut.

[0019] Therefore, the beneficial effects of the present application are as follows:

[0020] The present application effectively solves the problems of small space of the longitudinal seat cabin, difficulty in loading the pedal, and difficulty in controlling the loading angle. At the same time, the skin of the test machine is avoided to be damaged, and the integrity of the test machine is maintained to the greatest extent. The test device is simple and practical, and has strong operability. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is a schematic view of a longitudinal helicopter seat cabin pedal static strength test loading device.

[0022] Figure 2 It is a schematic view of a pedal loading claw.

[0023] Figure 3 It is a schematic view of a mounting lug.

[0024] Figure 4 It is a schematic view of a floor longitudinal beam.

[0025] Figure 5 It is a schematic view of a loading lug connecting rod.

[0026] Figure 6 It is a schematic view of a sensor connecting rod.

[0027] Figure 7 It is a schematic view of a fixed floor.

[0028] Figure 8 It is a schematic view of a loose nut.

[0029] Figure 9 It is a schematic view of a floor cross beam.

[0030] Figure 10Loading diagram for vertical column.

[0031] Figure 11 Loading diagram for support diagonal. DETAILED DESCRIPTION

[0032] In order to enable persons skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by persons skilled in the art without creative work should fall within the scope of protection of the present application.

[0033] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0034] In addition, the terms "mount", "set", "provided with", "connect", "connected", "sleeved" should be broadly understood. For example, it can be fixedly connected, detachably connected, or integrally constructed; it can be mechanically connected, or electrically connected; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the internal communication between two devices, elements or components. For persons skilled in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0035] The helicopter footrest static strength test loading device is described in detail in Figures 1-11 The helicopter footrest static strength test loading device is composed of a fixed floor 1, a footrest loading claw 2, a sensor 3, a sensor connecting rod 4, a loose sleeve 5, a loading ear connecting rod 6, a mounting ear 7, a loading vertical column 8, a floor longitudinal beam 9, a support diagonal 10, and a floor cross beam 11.

[0036] The fixed floor 1 is fixed with the cockpit floor through the countersunk hole 1-B. The floor longitudinal beam 9 and the floor cross beam 11 are fixed on the fixed floor 1 through the threaded hole 1-B on the floor and the threaded hole 9-B, 11-B on the floor longitudinal beam 9 and the floor cross beam 11. The loading column 8 is fixed by the mounting hole 11-A of the floor cross beam 11 and the mounting hole 8-C of the loading column 8. The mounting hole 8-B on the loading column 8 is fixed with the mounting hole 10-A of the support diagonal beam 10, and the mounting hole 9-A of the floor longitudinal beam 9 is fixed with the mounting hole 10-B of the support diagonal beam 10, so as to strengthen the support of the loading column. The mounting lug 7 is mounted at the mounting hole 8-A of the loading column 8. The appropriate mounting hole 8-A can be selected according to the actual situation to adjust the loading angle. The sensor connecting rod 4, the loose sleeve 5 and the loading lug connecting rod 6 are assembled. One end 6-A is connected to the mounting hole 7-A of the mounting lug 7. One end 4-B is connected with the sensor 3. The semicircular loading end 2-A of the footrest loading claw 2 is used to tighten the footrest support rod. The threaded joint 2-B of the footrest loading claw 2 is connected with the sensor. The loading end 2-A of the footrest loading claw 2 is in contact with the footrest support rod 12 by adjusting the loose sleeve 5. The footrest support rod 12 is loaded by rotating the loose sleeve 5.

[0037] The above only describes the preferred embodiments of the present application and is not used to limit the present application. The present application can have various changes and variations for those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A tandem helicopter cockpit footrest static strength testing loading device, characterized in that, include: Fixed floor, foot pedal loading claw, sensor, sensor connecting rod, tightening screw sleeve, loading ear connecting rod, mounting ear, loading column and floor beam; The fixed floor is installed on the cockpit floor; The floor beam is installed on the fixed floor, and two load-bearing columns are installed at both ends of the floor beam and stand on the fixed floor; Each of the two loading columns is fixed with a mounting lug, and the mounting lug is hinged to the loading lug connecting rod; One end of the tightening nut is connected to the loading lug connecting rod, and the other end is connected to the sensor connecting rod; The sensor connecting rod connects to one end of the sensor, and the other end of the sensor connects to the foot pedal loading claw. The pedal loading claw engages and locks with the pedal support rod.

2. The apparatus according to claim 1, characterized in that: The fixed floor is secured to the cockpit floor via countersunk holes.

3. The apparatus according to claim 2, characterized in that: The device also includes two floor longitudinal beams and two supporting diagonal rods; Two longitudinal floor beams are installed on the fixed floor and are perpendicular to and close to the transverse floor beams; Two supporting diagonal braces, one end of which is connected to the end of the floor longitudinal beam away from the floor transverse beam, and the other end of which is connected to the middle of the loading column.

4. The apparatus according to claim 3, characterized in that: The loading column is a U-shaped beam with multiple mounting holes for adjusting the angle of the mounting ears.

5. The apparatus according to claim 4, characterized in that: The semi-circular loading end of the foot pedal loading claw is fastened to the foot pedal support rod, and the threaded connector end of the foot pedal loading claw is connected to the sensor.

6. The apparatus according to claim 5, characterized in that: The tensioning sleeve has threaded sections at both ends, and the pedal support rod is loaded by rotating the tensioning sleeve.

Images