Passive telex brake system of helicopter
By introducing EHA technology into the helicopter braking system, a passive electric fly-by-wire braking system is developed, which combines electro-hydraulic and manual control mechanisms. This solves the problems of complex structure, heavy weight, high cost, and limited functionality in the absence of power in traditional helicopter braking systems. It enables normal braking function in both powered and unpowered states, improving the reliability and economy of the system.
Patent Information
- Application Number
- CN202511303508.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-12
- Publication Date
- 2025-12-12
AI Technical Summary
Traditional helicopter braking systems are complex in structure, heavy in weight, and expensive in cost. Existing passive fly-by-wire braking systems have limited functionality when there is no power.
The passive electric drive braking system based on EHA technology includes a brake command sensor, a cockpit control panel, a brake control box, a passive electric brake valve, and a brake device. It achieves braking function through electro-hydraulic control and is designed with a manual operating mechanism for operation in the absence of power.
It enables normal braking in both powered and unpowered states, improving the reliability and economy of the braking system, and enhancing mission reliability and energy-saving capabilities.
Smart Images
Figure CN121106684A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of helicopter brake systems, in particular to a passive electro-hydraulic brake system for helicopters. BACKGROUND
[0002] The conventional helicopter brake system mainly adopts a mechanical-hydraulic structure, which has the disadvantages of complex structure, large weight and high cost.
[0003] The passive electro-hydraulic brake system adopts EHA technology, EHA is the abbreviation of electro-hydraulic actuator, the four core components of EHA technology are servo motor, hydraulic pump, hydraulic actuator and electronic controller, the servo motor drives the hydraulic pump to realize mechanical energy output in the volumetric speed regulation mode, and the precise control of the actuator is completed, which has the advantages of simple structure, small weight and good economy, and is widely used in the mechanical and electrical systems of small and medium-sized unmanned aerial vehicles.
[0004] The present application applies the passive electro-hydraulic brake system based on EHA technology to the helicopter brake system, which can improve the reliability and economy of the brake system, and retain part of the mechanical structure to realize the brake function under the condition of no electricity on the ground, and has a positive effect on the task support and energy saving. SUMMARY
[0005] In order to solve the problems mentioned in the background art, the present application provides a passive electro-hydraulic brake system for helicopters, which is used for the functions of parking brake, brake release, deviation correction brake and the like of helicopters on the ground.
[0006] The present application discloses the following technical scheme: a passive electro-hydraulic brake system for helicopters, comprising a brake instruction sensor, a cockpit control panel, a brake control box, a passive electric brake valve and a brake device, the instruction sensor is installed on the left and right pilot foot pedals in the helicopter cockpit respectively, the instruction sensor is electrically connected with the brake control box, the brake control box is used for controlling the passive electric brake valve, the passive electric brake valve is used for providing hydraulic pressure to the left and right brake devices, a trigger button is arranged on the cockpit control panel, and the trigger button is used for transmitting voltage signals to the brake control box, and a manual control mechanism is designed on the passive electric brake valve.
[0007] Further, the brake instruction sensor is four pieces, and two pieces are matched for the left and right driver seats respectively, and are installed at the left foot and right foot pedals of the left and right pilots.
[0008] Further, the cockpit control panel is installed in the cockpit, the trigger button is three, and voltage signals for parking brake, brake release and power on / off of the brake system are sent to the brake control box respectively.
[0009] Further, the brake control box is two pieces, which are respectively installed on the passive electric control brake valve support, the brake control box receives voltage signals from the brake instruction sensor and the cockpit control panel, the brake control box converts the voltage signals into the instruction of controlling the output hydraulic pressure of the passive electric control brake valve, the passive electric control brake valve is provided with a pressure sensor for collecting the hydraulic pressure and transmitting to the brake control box, the brake control box carries out PID control on the brake pressure, and the brake control box also carries out BIT detection on the passive electric control brake valve.
[0010] Further, the passive electric control brake valve is two pieces, which respectively output the hydraulic pressure to the left and right brake devices to brake and release the brake.
[0011] Further, the manual operating mechanism is arranged at the end of the drive motor reducer of the passive electric control brake valve.
[0012] Compared with the prior art, the helicopter passive electric brake system has the beneficial effects as follows: 1. The brake control box receives voltage signals from the brake instruction sensor and the cockpit control panel button, and converts the voltage signals into the control signals for driving the left and right passive electric control brake valves, the passive electric control brake valves output the hydraulic pressure to the brake devices according to the control signals, so that the brake function is realized. 2. The brake control box collects the pressure output by the electric control brake valve, carries out PID control on the brake pressure, and carries out BIT detection on the passive electric control brake valve. 3. The brake system has the functions of parking brake, release brake and deviation correction brake in the power-on state, and can realize the functions of parking brake and release brake in the power-off state through the manual operating mechanism of the passive electric control brake valve. BRIEF DESCRIPTION OF DRAWINGS
[0013] Figure 1 The helicopter passive electric brake system of the application is shown in the figure. In the figure, 1 is a brake instruction sensor, 2 is a cockpit control panel, 3 is a brake control box, 4 is an electric control brake valve, and 5 is a brake device. DETAILED DESCRIPTION
[0014] As Figure 1As shown, a helicopter passive electric transmission brake system includes brake command sensor 1, cockpit control panel 2, brake control box 3, passive electric control brake valve 4 and brake device 5, the command sensor is respectively installed on the left and right pilot footboard in the helicopter cockpit, the command sensor is electrically connected with the brake control box 3, the brake control box 3 is used for controlling the passive electric control brake valve 4, the pilot steps on the footboard, the command sensor converts the displacement into the voltage signal proportional to the displacement, the brake control box 3 collects the voltage signals of the command sensor and the cockpit control panel 2 button, and converts the pressure signal into the control signal for controlling the passive electric control brake valve 4, the passive electric control brake valve 4 outputs the hydraulic pressure for closed-loop control, and the pressure is monitored; the passive electric control brake valve 4 is used for providing hydraulic pressure for left and right brake devices 5, and itself stores hydraulic oil, without needing to provide hydraulic source on the machine, according to the control command of the brake control box 3, the brake valve drives the oil to be supplemented into the brake device 5, to establish the brake pressure corresponding to the control signal, the cockpit control panel 2 is provided with a trigger button, the trigger button is used for transmitting the voltage signal to the brake control box 3, the cockpit control panel 2 is installed in the cockpit, the trigger button is three, respectively corresponding to send the voltage signal of the parking brake, the brake release and the brake system power on and off to the brake control box 3; a manual operating mechanism is designed on the passive electric control brake valve 4, the manual operating mechanism is arranged at the end of the drive motor reducer of the passive electric control brake valve 4, in the state of no electricity on the ground, through the operating handle, the passive electric control brake valve 4 can realize pressure building and pressure releasing, to realize the brake and brake release functions in the state of no electricity; the brake device 5 realizes the functions of the helicopter parking brake, brake release, differential brake and the like according to the hydraulic pressure output by the electric control brake valve.
[0015] The brake command sensor 1 is four, and two are matched for the left and right driving positions respectively, and are installed at the left foot and right foot pedals of the left and right pilots, the pilot steps on the footboard, the brake command sensor 1 converts the displacement into the voltage signal proportional to the displacement, and sends the voltage signal to the brake control box 3; the brake control box 3 is two, and is respectively installed on the support of the passive electric control brake valve 4, the brake control box 3 receives the voltage signals from the brake command sensor 1 and the cockpit control panel 2, the brake control box 3 converts the voltage signal into the command for controlling the output hydraulic pressure of the passive electric control brake valve 4, a pressure sensor is installed on the passive electric control brake valve 4 for collecting the hydraulic pressure and transmitting to the brake control box 3, the brake control box 3 carries out PID control on the brake pressure, and the brake control box 3 also carries out BIT detection on the passive electric control brake valve 4; the passive electric control brake valve 4 is two, and outputs the hydraulic pressure to the left and right brake devices 5, and outputs the corresponding hydraulic pressure to the left and right brake devices 5 according to the command of the brake control box 3 for braking and brake release.
[0016] Working principle: The brake control box 3 receives voltage signals from the brake command sensor 1 and the cockpit control panel 2, and converts these signals into control signals to drive the passive electronic brake valve 4. The passive electronic brake valve 4 outputs corresponding hydraulic pressure to the brake device 5 according to the control signal to achieve the braking function. The drive component of the passive electronic brake valve 4 is designed with a manual operation mechanism, allowing the braking system to be stopped and released manually when there is no power.
[0017] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.
Claims
1. A passive fly-by-wire braking system for helicopters, characterized in that: The system includes a brake command sensor (1), a cockpit control panel (2), a brake control box (3), a passive electronic brake valve (4), and a brake device (5). The command sensor is installed on the left and right pilot foot pedals in the helicopter cockpit. The command sensor is electrically connected to the brake control box (3). The brake control box (3) is used to control the passive electronic brake valve (4). The passive electronic brake valve (4) is used to provide hydraulic pressure to the left and right brake devices (5). The cockpit control panel (2) is equipped with a trigger button, which is used to transmit a voltage signal to the brake control box (3). The passive electronic brake valve (4) is designed with a manual operation mechanism.
2. The helicopter passive fly-by-wire braking system according to claim 1, characterized in that: The brake command sensor (1) consists of four units, with two units for each of the left and right driver's seats, and is installed at the left and right foot pedals of the left and right pilots.
3. The helicopter passive fly-by-wire braking system according to claim 1, characterized in that: The cockpit control panel (2) is installed in the cockpit. There are three trigger buttons, which respectively send voltage signals to the brake control box (3) for stopping the brake, releasing the brake, and powering on / off the brake system.
4. The helicopter passive fly-by-wire braking system according to claim 1, characterized in that: The brake control box (3) consists of two parts, which are respectively installed on the support of the passive electric brake valve (4). The brake control box (3) receives voltage signals from the brake command sensor (1) and the cockpit control panel (2). The brake control box (3) converts the voltage signals into commands to control the output hydraulic pressure of the passive electric brake valve (4). The passive electric brake valve (4) is equipped with a pressure sensor to collect hydraulic pressure and transmit it to the brake control box (3). The brake control box (3) performs PID control on the brake pressure and also performs BIT detection on the passive electric brake valve (4).
5. The helicopter passive fly-by-wire braking system according to claim 1, characterized in that: The passive electronic brake valve (4) consists of two parts, which respectively output hydraulic pressure to the left and right brake devices (5) to brake and release the brake.
6. The helicopter passive fly-by-wire braking system according to claim 1, characterized in that: The manual operating mechanism is located at the end of the drive motor reducer of the passive electronic brake valve (4).