Helicopter shock absorbing step device

Abstract

The present application relates to the field of helicopter control system damping, in particular to a helicopter damping footrest device. The device comprises: a damping footrest (1) with a footrest pedal (4), a footrest mounting cross pipe (2), a footrest mounting vertical rod (3); the damping footrest (1) is mounted on the footrest mounting vertical rod (3) through the mounting cross pipe (2); the damping footrest (1) is integrated into a counter-resonance vibration isolation design.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of helicopter control system damping, in particular to a helicopter damping footrest device. BACKGROUND

[0002] The complexity of the aerodynamic environment and the transmission system of the helicopter determines the complexity of the vibration problem of the helicopter. The vibration problem has always been an important problem in the design and use of the helicopter. The footrest is a control device for the pilot to manipulate the tail rotor. If the vibration level of the footrest is too high, it will seriously affect the comfort of the pilot. The footrest is connected to the tail rotor through a control lever system. Therefore, the footrest is not only directly affected by the vibration of the tail rotor, but also affected by the vibration of the aircraft body transmitted through the control lever system. Therefore, the source of the footrest vibration is relatively complex.

[0003] At present, the vibration of the cockpit of domestic helicopters is paid more attention to, but the vibration of the control system and the footrest is paid less attention to. Therefore, the damping design of the control system and the footrest is generally not considered in the design of the helicopter control system and the footrest.

[0004] The existing helicopter footrest does not consider the requirement of damping. The existing helicopter footrest pedal is directly installed on the footrest installation vertical rod through the installation cross pipe. Even some helicopters cancel the design of the footrest pedal in the design, and the installation cross pipe is directly installed on the footrest installation vertical rod. The pilot directly steps on the installation cross pipe to manipulate, so that the pilot directly bears the vibration of the footrest, thereby causing the pilot to have a poor flight experience. SUMMARY

[0005] The purpose of the present application is to effectively reduce the vibration of the control lever system to the footrest and effectively improve the vibration level of the pilot's footrest under the premise of not reducing the stiffness of the footrest and the control system, so as to improve the driving comfort of the helicopter pilot.

[0006] The technical scheme of the present application:

[0007] A helicopter damping footrest device, comprising: a damping footrest having a footrest pedal, a footrest installation cross pipe, and a footrest installation vertical rod.

[0008] The damping footrest is installed on the footrest installation vertical rod through the installation cross pipe. The damping footrest is designed with anti-resonance vibration isolation.

[0009] The upper and lower ends of the damping footrest are provided with counterweight pieces. The weight of the counterweight pieces is adjusted to achieve the anti-resonance effect of the damping footrest.

[0010] The damping footrest comprises: a counterweight piece, a connecting arm, an elastic element, and a connecting rod.

[0011] The connecting rod is divided into an upper connecting rod and a lower connecting rod; the connecting arm is a frame structure with an open end, divided into an upper connecting arm and a lower connecting arm, the open end of the upper connecting arm is provided with a small sleeve, the small sleeve is sleeved on the installation horizontal pipe, the upper cross beam of the upper connecting arm is fixedly connected with a counterweight piece, and the bottom ends of the two side beams of the upper connecting arm are fixedly connected with the upper end side wall of the foot pedal through the upper connecting rod;

[0012] The open end of the lower connecting arm is provided with a large sleeve, the large sleeve is sleeved on the small sleeve through an annular elastic element, the installation horizontal pipe passes through the small sleeve and locks the large sleeve, the elastic element and the small sleeve, the lower cross beam of the lower connecting arm is fixedly connected with a counterweight piece, and the bottom ends of the two side beams of the lower connecting arm are fixedly connected with the lower end side wall of the foot pedal through the lower connecting rod.

[0013] The elastic element is vulcanized rubber.

[0014] The counterweight piece is used for adjusting the anti-resonance frequency, and inertia force is generated along with the movement of the upper and lower connecting rocker arms, so as to offset the vibration transmitted to the foot pedal, thereby reducing the vibration on the foot pedal.

[0015] The two devices are a pair of devices installed on an airplane.

[0016] The foot pedal adopts a hollow structure.

[0017] The upper connecting arm and the lower connecting arm form a lever system with the foot pedal and the counterweight piece.

[0018] The beneficial effects of the present application are:

[0019] I. The vibration reduction foot pedal device is designed based on the existing helicopter foot pedal installation interface, and the structure is more compact and more widely applicable to the installation of the existing helicopter foot pedal.

[0020] II. The vibration reduction foot pedal device adopts mechanical connection, has high connection rigidity, and improves the reliability of the vibration reduction foot pedal device and facilitates disassembly, maintenance and assembly.

[0021] III. The vibration reduction foot pedal device is designed with a counterweight piece, which can be adjusted according to the actual vibration characteristics of different helicopter cockpits, the dynamics of the vibration reduction system can be changed by adjusting the mass of the piece, and the vibration reduction foot pedal can be applied to helicopters with different vibration characteristics. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a three-dimensional assembly drawing of the helicopter vibration reduction foot pedal device.

[0023] Figure 2 It is an assembly relationship drawing of the helicopter vibration reduction foot pedal device.

[0024] Figure 3 It is a three-dimensional explosion drawing of the helicopter vibration reduction foot pedal device. DETAILED DESCRIPTION

[0025] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only 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 those skilled in the art without creative work fall within the protection scope of the present application.

[0026] According to the current analysis of the use of helicopters, the domestic helicopters also have different degrees of footrest vibration. As an important part of the helicopter control system, the footrest directly faces the pilot, and the vibration will directly affect the vibration level and the driving comfort of the pilot. The damping footrest structure effectively reduces the vibration of the control rod system to the footrest and effectively improves the vibration level of the pilot's footrest, so as to improve the driving comfort of the pilot.

[0027] In order to make the helicopter damping footrest simple in structure, high in reliability and strong in universality, based on the current installation interface and vibration characteristics of the field helicopter footrest, a helicopter damping footrest device is provided.

[0028] The device comprises: a damping footrest 1 with a footrest pedal 4, a footrest installation horizontal pipe 2, and a footrest installation vertical rod 3.

[0029] The damping footrest 1 is installed on the footrest installation vertical rod 3 through the installation horizontal pipe 2. The damping footrest 1 is integrated with the anti-resonance vibration isolation design.

[0030] The upper and lower ends of the damping footrest 1 are provided with counterweight pieces. The weight of the counterweight pieces is adjusted to achieve the anti-resonance effect of the damping footrest.

[0031] The damping footrest 1 comprises: counterweight pieces, connecting arms, elastic elements, and connecting rods.

[0032] The connecting rods are divided into upper connecting rods and lower connecting rods. The connecting arms are frame structures with one end open, and are divided into upper connecting arms and lower connecting arms. The open ends of the upper connecting arms are each provided with a small sleeve pipe, the small sleeve pipe is sleeved on the installation horizontal pipe 2, the upper crossbeam of the upper connecting arm is fixedly connected with the counterweight pieces, and the bottom ends of the two side beams of the upper connecting arm are fixedly connected with the upper end side wall of the footrest pedal 4 through the upper connecting rods. The open end of the lower connecting arm is provided with a large sleeve pipe, the large sleeve pipe is sleeved on the small sleeve pipe through the annular elastic element, the installation horizontal pipe 2 passes through the small sleeve pipe and locks the large sleeve pipe, the elastic element and the small sleeve pipe, the lower crossbeam of the lower connecting arm is fixedly connected with the counterweight pieces, and the bottom ends of the two side beams of the lower connecting arm are fixedly connected with the lower end side wall of the footrest pedal 4 through the lower connecting rods. Embodiment

[0033] To reduce pedal vibration and improve pilot comfort, a vibration-damping helicopter pedal was designed based on the anti-resonance principle to replace the original non-vibration-damping pedals. Figure 2 As shown, to improve the versatility of the vibration-damping foot pedals, the design is based on the existing helicopter foot pedal mounting interface. The vibration-damping foot pedal 1 is mounted on the foot pedal mounting pole 3 via the mounting cross tube 2. Figure 3 As shown, the vibration damping foot pedal 1 mainly comprises four parts: vibration damping foot pedal 1, foot pedal mounting horizontal tube 2, foot pedal mounting vertical rod 3, and foot pedal 4; foot pedal 4 is used by the pilot to step on it during operation; upper connecting arm 10 and lower connecting arm 11 are used to connect the counterweight plate 7, which moves the upper and lower connecting rocker arms during vibration and generates sufficient inertial force; the counterweight plate 7 is used to adjust the anti-resonance frequency, and at the same time, it generates inertial force with the movement of the upper and lower connecting rocker arms to counteract the vibration transmitted to the foot pedal 4, thereby reducing the vibration on the foot pedal 4; the elastic element 9 (vulcanized rubber) mainly provides torsional stiffness for the upper connecting arm 10 and lower connecting arm 11; the connecting rod 5 is mainly used to connect the foot pedal 4, the upper connecting arm 10, and the lower connecting arm 11. The counterweight 7 is connected and fixed to the upper connecting arm 10 and the lower connecting arm 11 respectively by connecting bolts 8. The upper connecting arm 10 and the lower connecting arm 11 are connected by an elastic element (vulcanized rubber). The foot pedal 4 is connected and fixed to the upper connecting arm 10 and the lower connecting arm 11 by connecting rod 5 and connecting bolts 6, forming a complete vibration-damping foot pedal 1 (one on each side). The vibration-damping foot pedal 1 is assembled with the foot pedal mounting horizontal tube 2 and the foot pedal mounting vertical rod 3, and the foot pedal mounting vertical rod 3 is connected to the machine body structure.

[0034] The vibration damping foot pedal device is based on the existing helicopter foot pedal installation interface and takes into account the helicopter foot pedal control stiffness requirements. Without reducing the foot pedal connection stiffness, it incorporates anti-resonance vibration isolation design into the foot pedal structure according to the vibration characteristics of the foot pedal, thereby ensuring that the seat has the characteristics of high connection stiffness, compact structure, high reliability and strong versatility.

[0035] Mechanism of action of the present invention:

[0036] When the pedal mounting pole 3 vibrates, the pedal mounting tube 2 vibrates accordingly, further driving the upper connecting arm 10 and the lower connecting arm 11 to move. Because the upper connecting arm 10 and the lower connecting arm 11 form a lever system with the pedal 4 and the counterweight 7, the upper connecting arm 10 and the lower connecting arm 11 rotate relative to each other around the connecting hole of the pedal mounting tube 2. The counterweight 7 moves together with the upper connecting arm 10 and the lower connecting arm 11. At this time, the counterweight 7 and the upper connecting arm 10 and the lower connecting arm 11 generate inertial force, which counteracts the dynamic load from the pedal mounting tube 2, reduces the vibration level of the pedal 4, and reduces the actual vibration level experienced by the pilot when operating the pedals, thereby improving the pilot's operating comfort.

[0037] The above merely describes specific embodiments of the present application, and the detailed description of the present application is not exhaustive of the conventional technology. However, the protection scope of the present application is not limited to this, and any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered by the protection scope of the present application. The protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A helicopter vibration damping foot pedal device, characterized in that, include: Vibration-damping pedal (1), pedal mounting horizontal tube (2), pedal mounting vertical pole (3), pedal pedal (4). The vibration-damping pedal (1) is mounted on the pedal mounting pole (3) via the pedal mounting horizontal tube (2); The vibration damping pedal (1) includes: a counterweight plate (7), an upper connecting arm (10), a lower connecting arm (11), an elastic element (9), an upper connecting rod, and a lower connecting rod; The upper connecting arm (10) and the lower connecting arm (11) are frame structures with one end open; Each of the open ends of the upper connecting arm (10) is provided with a small sleeve, which is fitted onto the foot pedal mounting cross tube (2). The upper cross beam of the upper connecting arm (10) fixes the counterweight plate (7). The bottom ends of the two side beams of the upper connecting arm (10) are fixed to the upper side wall of the foot pedal (4) through the upper connecting rod. The open end of the lower connecting arm (11) is provided with a large sleeve. The large sleeve is fitted onto the small sleeve through the annular elastic element (9). The foot pedal mounting cross tube (2) passes through the small sleeve and locks the large sleeve, the elastic element (9) and the small sleeve. The lower cross beam of the lower connecting arm (11) fixes the counterweight plate (7). The bottom ends of the two side beams of the lower connecting arm (11) are fixed to the lower side wall of the foot pedal (4) through the lower connecting rod.

2. The apparatus according to claim 1, characterized in that, The elastic element (9) is vulcanized rubber.

3. The apparatus according to claim 1, characterized in that, The counterweight (7) is used to adjust the anti-resonance frequency, and at the same time, as the upper connecting arm (10) and the lower connecting arm (11) move, an inertial force is generated to counteract the vibration transmitted to the foot pedal (4).

4. The apparatus according to claim 1, characterized in that, The devices are a pair and are installed on the aircraft.

5. The apparatus according to claim 1, characterized in that, The foot pedal (4) has a hollow structure.

6. The apparatus according to claim 1, characterized in that, The upper connecting arm (10) and the lower connecting arm (11) form a lever system with the foot pedal (4) and the counterweight (7).

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