Aircraft canopy opening and closing control device and control method

Abstract

The present invention relates to an aircraft canopy opening and closing control device and a control method, and belongs to the field of aircraft electromechanical control technology. An aircraft canopy opening and closing control device comprises a front cabin canopy opening and closing switch and a rear cabin canopy opening and closing switch respectively arranged in the front cabin and the rear cabin of the aircraft, and the canopy opening and closing switch can realize the state switching of the three positions of opening, closing and neutral; it also comprises a canopy opening and closing button box arranged outside the cabin, which comprises a canopy opening and closing button; when the canopy is in an open or closed state, the canopy opening and closing is controlled by the canopy opening and closing button box. The present invention has the following advantages: it realizes the integration of canopy opening and closing control into electromechanical load power distribution equipment, reduces the number of airborne finished products and reduces the weight of finished products, improves the execution efficiency of the electric mechanism, and all relevant parameters can be stored and recorded in real time, which is convenient for the maintenance of the canopy system in the later stage.

Description

Technical Field

[0001] The invention relates to an aircraft canopy opening and closing control device and a control method, belonging to the technical field of aircraft electromechanical control. Background Art

[0002] Most of the existing aircraft canopy opening and closing systems use a separate "relay control box" and "canopy control box" to control the canopy lifting and lowering electric mechanism. The opening and closing timing control of the canopy is realized by the relay inside the relay control box through interlocking. The rear lifting and lowering electric mechanism is directly driven by the canopy control box. The control box has a single function. When the transient value of the rear driving voltage exceeds the upper limit of the relay withstand voltage, long-term on and off will cause relay contact ablation, which is not conducive to the maintenance of the canopy system in the later stage and cannot meet the requirements of miniaturization, integration and high reliability of airborne products. Summary of the invention

[0003] The purpose of the present invention is to provide an aircraft canopy opening and closing control device, which replaces the traditional single-function control box and integrates the canopy opening and closing control function into the electromechanical load distribution equipment for unified management.

[0004] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: an aircraft canopy opening and closing control device, comprising a front cabin canopy opening and closing switch and a rear cabin canopy opening and closing switch respectively arranged in the front cabin and the rear cabin of the aircraft, and the canopy opening and closing switch can realize the state switching of the three positions of open cabin, closed cabin and neutral cabin; it also includes a canopy opening and closing button box arranged outside the cabin, which includes a cabin opening button and a cabin closing button; when the canopy is in the open or closed state, the canopy opening and closing control is realized by the canopy opening and closing button box.

[0005] Preferably, the cockpit cover opening and closing functions of the front cabin cover opening and closing switch, the rear cabin cover opening and closing switch and the cover opening and closing button box are integrated into the electromechanical load power distribution equipment.

[0006] Preferably, the front cabin cover opening and closing switch and the rear cabin cover opening and closing switch are both pull-type switches. When the switch is in the neutral position, the pilot only needs to pull the switch in the vertical direction to unlock it, and then toggle the switch forward or backward to control the opening or closing of the canopy.

[0007] Another object of the present invention is to provide a method for optimizing the opening and closing control of an aircraft canopy, using the above-mentioned aircraft canopy opening and closing control device, comprising the following steps:

[0008] (1) Initialization of electromechanical load distribution equipment;

[0009] (2) The electromechanical load distribution equipment collects data and collects the hatch cover opening, closing and unlocking signals;

[0010] (3) When the “hatch cover opening and closing unlocking position signal” is valid, the cabin opening and closing discrete quantity signals inside and outside the cabin and the opening or closing position signal of the lifting electric mechanism are collected in real time;

[0011] (4) Comprehensively solve and obtain the canopy opening and closing control instructions, and output the opening and closing control signals to drive the rear-end electric mechanism to perform extension and retraction operations;

[0012] (5) After the canopy is raised or lowered into position, the electromechanical load distribution equipment releases the residual energy in the coil inside the electric mechanism through the internal energy release circuit.

[0013] Preferably, in step (1), when the electromechanical load power distribution equipment is initialized or fails, the output control signal: "electric actuator extension control signal" is invalid, and "electric actuator retraction control signal" is invalid.

[0014] Preferably, in step (2), when the hatch cover opening and closing unlocking signal is invalid, the output control signal: "cabin cover lifting electric actuator extension control signal" is invalid, and "electric actuator retraction control signal" is invalid.

[0015] Preferably, when the canopy "open" command signal and the "close" command signal are both valid, the canopy lifting electric mechanism is controlled by an interlocking circuit to maintain the previous state, i.e., the control logic executes the canopy opening or closing operation).

[0016] Compared with the prior art, the present invention has the following advantages: the cockpit cover opening and closing control is integrated into the electromechanical load power distribution equipment, the traditional single-function relay box control is eliminated, the electromechanical load power distribution equipment realizes the lifting and lowering control of the cockpit cover by collecting the cockpit cover opening and closing instructions and the opening and closing in place signals, the number of airborne finished products and the weight of finished products are reduced, the execution efficiency of the electric mechanism is improved, and the relevant parameters can be stored and recorded in real time, which is convenient for the later maintenance of the cockpit cover system. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a control flow chart of an embodiment of the present invention. DETAILED DESCRIPTION

[0018] The following is combined with Figure 1The present invention is further described in detail: a method for controlling the opening and closing of an aircraft canopy, which eliminates a relay control box with a single function and integrates the canopy opening and closing function into an electromechanical load power distribution device for management. After the pilot pushes and pulls the lock rod inside the cockpit to unlock the canopy in place, the electromechanical load power distribution device collects the "canopy opening and closing unlocking in place signal" as an access condition for the canopy opening and closing control, and collects the cabin opening and closing discrete quantity signals inside and outside the cabin and the opening or closing in place signal of the lifting electric mechanism in real time, obtains the canopy opening and closing control command after comprehensive calculation, outputs the opening and closing control signal to drive the rear end electric mechanism to perform the extension and retraction operation, and after the canopy is lifted and lowered in place, the electromechanical load power distribution device releases the residual energy of the coil inside the electric mechanism through the internal energy release circuit.

[0019] The specific control technical means of the present invention are as follows (wherein the hatch cover opening and closing instruction interpretation, hatch cover opening and closing control requirements, initialization and fault handling are all uniformly controlled and managed by the electromechanical load distribution equipment).

[0020] 1. Interpretation of hatch cover opening and closing instructions

[0021] 1) When the "canopy opening command signal" is invalid and the "canopy closing command signal" is invalid, the canopy "open" command and the canopy "close" command are invalid;

[0022] 2) When the "canopy opening command signal" is valid and the "canopy closing command signal" is invalid, the canopy "open" command is valid and the canopy "close" command is invalid;

[0023] 3) When the "canopy opening command signal" is invalid and the "canopy closing command signal" is valid, the canopy "open" command is invalid and the canopy "close" command is valid;

[0024] 4) When the "canopy opening command signal" and the "canopy closing command signal" are valid, the canopy "open" command and the canopy "close" command will remain in the previous state.

[0025] 2. Requirements for hatch cover opening and closing control

[0026] 1) When the hatch cover opening, closing and unlocking signal is invalid

[0027] Output control signal: "Cockpit cover lifting electric actuator extension control signal" is invalid, and "Electric actuator retraction control signal" is invalid.

[0028] 2) When the hatch cover opening, closing and unlocking signal is valid

[0029] When the canopy "open" command is valid and the "canopy lifting electric actuator extended to position signal" is invalid, the output control signal: "electric actuator extension control signal" is valid and "electric actuator retraction control signal" is invalid.

[0030] When the canopy "close" command is valid and the "canopy lifting electric actuator retracted signal" is invalid, the output control signal: "electric actuator extension control signal" is invalid, and the "electric actuator retraction control signal" is valid.

[0031] When the canopy "open" command and the "close" command are valid at the same time, the canopy lifting and lowering electric mechanism is kept in the previous state through the control signal interlock circuit.

[0032] In other cases, the output control signal: "Electric actuator extension control signal" is invalid, and "Electric actuator retraction control signal" is invalid.

[0033] 3. Initialization and troubleshooting

[0034] When the electromechanical load power distribution equipment is initialized or fails, the output control signal: "Electric actuator extension control signal" is invalid, and "Electric actuator retraction control signal" is invalid.

[0035] The details are as follows:

[0036] A front cabin cover opening and closing switch and a rear cabin cover opening and closing switch are arranged inside the cockpit of a certain type of aircraft, and a cabin cover opening and closing button box is arranged outside the cockpit. Among them, the front cabin cover opening and closing switch and the rear cabin cover opening and closing switch are both single-pole three-position switches. The switch is a pull-type switch. The three positions correspond to the three states of open cabin, neutral cabin and closed cabin, respectively, and the state switching of the three positions of open cabin, closed cabin and neutral cabin can be realized. When the switch is in the neutral position, the pilot only needs to pull the switch in the vertical direction to unlock it, and then toggle the switch forward or backward to realize it. The canopy opening or closing control operation is now performed; the canopy opening and closing button box is equipped with two open and close buttons. When any switch in the cabin is turned to the open position or the "open" button on the button box outside the cabin is pressed, the "canopy opening command signal" is valid. When any switch in the cabin is turned to the closed position or the "close" button on the button box outside the cabin is pressed, the "canopy closing command signal" is valid. When the canopy is in the open or closed state, the ground crew can control the opening and closing of the canopy through the canopy opening and closing button box installed outside the cabin.

[0037] When the "canopy opening and closing unlocking signal" is valid, the electromechanical load distribution equipment implements the entire operation process of opening and closing the canopy through the following steps.

[0038] (1) The “electric mechanism extended to the end signal” is invalid, and the cockpit cover opening function is realized:

[0039] When the "cockpit cover opening command signal" is valid and the "cockpit cover closing command signal" is invalid, the electromechanical load power distribution equipment outputs an opening control signal to the electric mechanism to realize the opening function of the cockpit cover. When the "cockpit cover extended to the full signal" is valid, the electromechanical load power distribution equipment releases the residual energy of the motor coil inside the electric mechanism through the energy release circuit inside the electromechanical load power distribution equipment, and stops outputting the opening control signal to the outside.

[0040] (2) The “electric mechanism retracted to position signal” is invalid, and the cockpit cover closing function is realized:

[0041] When the "canopy closing command signal" is valid and the "canopy opening command signal" is invalid, the electromechanical load power distribution equipment outputs a closing control signal to the electric mechanism to realize the canopy closing function. When the "canopy retracting signal" is valid, the electromechanical load power distribution equipment releases the residual energy of the motor coil inside the electric mechanism through the energy release circuit inside the electromechanical load power distribution equipment and stops outputting the closing control signal to the outside.

Claims

1. An aircraft canopy opening and closing control device, characterized in that: It includes a front cabin cover opening and closing switch and a rear cabin cover opening and closing switch respectively arranged in the front cabin and the rear cabin of the aircraft, and the cabin cover opening and closing switch can realize the state switching of the three positions of opening, closing and neutral; it also includes a cabin cover opening and closing button box arranged outside the cabin, which includes cabin opening and cabin closing buttons; when the cabin cover is in the open or closed state, the cabin cover opening and closing button box is used to realize the control of the opening and closing of the cabin cover; the cabin cover opening and closing function is integrated in the electromechanical load power distribution equipment; A control method for an aircraft canopy opening and closing control device comprises the following steps: (1) Initialization of electromechanical load distribution equipment; (2) The electromechanical load distribution equipment collects data and collects the hatch cover opening, closing and unlocking signals; (3) When the "hatch cover opening and closing unlocking signal" is valid, the cabin opening and closing discrete quantity signals inside and outside the cabin and the opening or closing signal of the lifting electric mechanism are collected in real time; (4) Comprehensively solve and obtain the canopy opening and closing control instructions, and output the opening and closing control signals to drive the rear-end electric mechanism to perform extension and retraction operations; (5) After the canopy is raised or lowered into position, the electromechanical load distribution equipment releases the residual energy in the coil inside the electric mechanism through the internal energy release circuit.

2. The aircraft canopy opening and closing control device according to claim 1, characterized in that: The cockpit cover opening and closing functions of the front cabin cover opening and closing switch, the rear cabin cover opening and closing switch and the cover opening and closing button box are integrated into the electromechanical load power distribution equipment.

3. The aircraft canopy opening and closing control device according to claim 1, characterized in that: The front cabin cover opening and closing switch and the rear cabin cover opening and closing switch are both pull-type switches. When the switch is in the neutral position, the pilot only needs to pull the switch in the vertical direction to unlock it, and then push the switch forward or backward to open or close the canopy.

4. The aircraft canopy opening and closing control device according to claim 1, characterized in that: In step (1), when the electromechanical load power distribution equipment is initialized or fails, the output control signals are: "electric actuator extension control signal" is invalid, and "electric actuator retraction control signal" is invalid.

5. The aircraft canopy opening and closing control device according to claim 1, characterized in that: In step (2), when the hatch cover opening and closing unlocking signal is invalid, the output control signals are: "cabin cover lifting electric actuator extension control signal" is invalid, and "electric actuator retraction control signal" is invalid.

6. The aircraft canopy opening and closing control device according to claim 1, characterized in that: When the canopy "open" command and the "close" command are valid at the same time, the canopy lifting and lowering electric mechanism is kept in the previous state through the control signal interlock circuit.

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