CN115057002B - Automatic following measuring device for automatic accelerator of airplane - Google Patents
Automatic following measuring device for automatic accelerator of airplane Download PDFInfo
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- CN115057002B CN115057002B CN202210960424.7A CN202210960424A CN115057002B CN 115057002 B CN115057002 B CN 115057002B CN 202210960424 A CN202210960424 A CN 202210960424A CN 115057002 B CN115057002 B CN 115057002B
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- 210000000078 claw Anatomy 0.000 claims description 25
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- 239000004020 conductor Substances 0.000 claims description 6
- 239000012212 insulator Substances 0.000 claims description 5
- 230000004308 accommodation Effects 0.000 claims description 4
- 238000004891 communication Methods 0.000 claims description 4
- 238000005259 measurement Methods 0.000 abstract description 8
- 238000000034 method Methods 0.000 description 11
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
- B64D31/04—Initiating means actuated personally
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Abstract
An automatic follow-up measurement device for an aircraft auto throttle, comprising: throttle drive jack catch, throttle drive jack catch includes: the connecting part is connected with the driving mechanism, and the driving part is connected with the throttle lever in a matching way; the jack catch linkage part is arranged on the throttle lever; the jaw linkage member includes: the accommodating cavity is used for accommodating the driving part; the accommodating cavity is provided with: the first connecting surface is used for pulling the accelerator driving clamping jaw, and the second connecting surface is used for pushing the accelerator driving clamping jaw; the accommodating cavity is also provided with a sliding space for the driving part to slide in the accommodating cavity so as to be separately connected with the first connecting surface or the second connecting surface; the follow-releasing driving mechanism is used for driving the first connecting surface or the second connecting surface to be far away from the driving part so as to release the automatic follow of the airplane throttle; and a measuring mechanism. The structure can effectively solve the problem that a measuring device for measuring the driving force required by switching the accelerator push rod of the airplane from automatic cruise control to manual control is lacked in the prior art.
Description
Technical Field
The invention relates to the technical field of airplane accelerator push rod detection, in particular to an automatic following measuring device for an airplane automatic accelerator.
Background
In the aircraft manufacturing and assembling process, after the accelerator platform is installed, the force value of the accelerator rod acting in the running state needs to be detected, and whether the installation of the accelerator platform is qualified or not is judged according to whether the force value meets the design requirement or not. In the prior art, a manipulator is usually adopted to pull the throttle lever so as to realize the detection work of the throttle lever. However, in the conventional detection items of the aircraft throttle system, no attention is paid to detection of the magnitude of the driving force required for detecting the switching of the aircraft throttle push rod from the automatic cruise control to the manual control. If the force required by the switching process of the accelerator push rod of the airplane is too small, the problem of releasing the automatic cruise by mistake is easily caused. If the force required by the switching process of the accelerator push rod of the airplane is too large, the use experience of taking over the accelerator of the airplane by an operator is influenced. Therefore, in view of the use safety and user experience of the airplane throttle system, an automatic following measuring device for the airplane automatic throttle is needed so as to measure the driving force magnitude required by the airplane throttle push rod to be switched from automatic cruise control to manual control.
Disclosure of Invention
The invention aims to provide an automatic following measuring device for an automatic accelerator of an airplane, and solves the problem that a potential safety hazard exists in an airplane accelerator system due to the fact that a measuring device for measuring the driving force required by the conversion from automatic cruise to manual control of an accelerator push rod of the airplane is lacked in the prior art. The invention thus provides an automatic following measurement device for an aircraft automatic throttle, comprising:
throttle drive jack catch, throttle drive jack catch includes: the connecting part is connected with the driving mechanism, and the driving part is connected with the throttle lever in a matching way;
the clamping jaw linkage part is arranged on the throttle rod; the jaw linkage part includes: the throttle connecting part is used for connecting the throttle lever; the accommodating cavity is provided with: the first connecting surface is used for pulling the accelerator driving clamping jaw, and the second connecting surface is used for pushing the accelerator driving clamping jaw; the accommodating cavity is also provided with a sliding space for the driving part to slide in the accommodating cavity so as to be separately connected with the first connecting surface or the second connecting surface;
the follow-releasing driving mechanism is used for driving the first connecting surface or the second connecting surface to be far away from the driving part so as to release the automatic follow of the aircraft accelerator;
and the measuring mechanism is used for measuring whether the aircraft accelerator releases the automatic following or not and recording the driving force value applied to the first connecting surface or the second connecting surface by the following releasing driving mechanism when the automatic following is released.
Optionally, the cross section of the accelerator driving clamping jaw is of an i-shaped structure, and an opening for inserting the accelerator driving clamping jaw into the accommodating cavity is formed in the accommodating cavity.
Optionally, the follow-up releasing driving mechanism includes: a first push rod and a second push rod;
the first push rod is in driving contact with the first connecting surface under the condition that the claw linkage component pulls the accelerator to drive the claws, and the first connecting surface of the accommodating cavity is driven to be far away from the driving part;
and under the condition that the claw linkage part pushes the throttle rod, the second push rod is in driving contact with the second connecting surface, and the second connecting surface of the accommodating cavity is driven to be far away from the driving part.
Optionally, the number of the first push rods is two, and the first push rods are arranged on the driving part and symmetrically arranged at two sides of the opening; and/or the presence of a gas in the atmosphere,
the two second push rods are arranged on the driving portion and symmetrically arranged on two sides of the opening.
Optionally, a first electromagnetic mechanism and a second electromagnetic mechanism are respectively disposed on the first connection surface and the second connection surface, and the driving portion is a magnetic component with a magnetic property opposite to that of the first electromagnetic mechanism and that of the second electromagnetic mechanism;
the first electromagnetic mechanism is controlled to generate a magnetic field to apply a first magnetic force towards the driving part to make the first magnetic force far away from the first connecting surface, and the first connecting surface of the accommodating cavity is driven to far away from the driving part;
the second electromagnetic mechanism is controlled to generate a magnetic field to apply a first magnetic force towards the driving portion to enable the driving portion to be far away from the second connecting surface, and the second connecting surface of the accommodating cavity is driven to be far away from the driving portion.
Optionally, the measuring mechanism includes:
the driving force sensor is arranged on the follow-up releasing driving mechanism and used for measuring a driving force value generated by the follow-up releasing driving mechanism;
the accelerator lever driving force sensor is arranged on the accelerator lever and used for detecting a driving force value generated by the accelerator lever, and when the driving force of the accelerator lever is reduced to zero, the automatic following of the airplane accelerator is released.
Optionally, the measuring mechanism includes:
the driving force sensor is arranged on the follow-up releasing driving mechanism and used for measuring a driving force value generated by the follow-up releasing driving mechanism;
and the accelerator lever direction sensor is arranged on the accelerator lever and used for detecting the moving direction of the accelerator lever, and when the moving direction of the accelerator lever is opposite to the automatic following direction of the accelerator lever, the airplane accelerator is relieved from automatic following.
Optionally, the accommodating cavity includes: a first portion and a second portion connected together by an insulator; the first part and the second part are both made of conductive materials; a rotating gap for the driving part to rotate is formed between the driving part and the inner cavity wall of the accommodating cavity and is close to one side of the insulating part;
the automatic following measuring device for the aircraft automatic throttle further comprises: a circuit detection mechanism; the circuit detection mechanism includes: detection circuits connected to the first and second portions, respectively; when the accelerator driving claw is separated from the preset track, the driving part is respectively connected with the first part and the second part so as to enable the detection circuit to be conducted, and the driving mechanism controller controls the driving mechanism to stop acting.
Optionally, the automatic following measuring device for the aircraft automatic throttle further includes:
the push rod controller is respectively in communication connection with the first push rod and the second push rod;
the push rod controller is used for respectively controlling the two first push rods arranged on the same side of the accommodating cavity to independently stretch and retract so as to enable the driving part not to incline any more and to be respectively connected with the first part and the second part; and/or the presence of a gas in the gas,
the push rod controller is used for respectively controlling two second push rods arranged on the same side of the accommodating cavity to independently stretch and retract so that the driving part does not incline any more and is respectively connected with the first part and the second part.
The user controls one of the two first push rods to act independently through the push rod controller, or controls one of the two second push rods to act independently through the push rod controller, so that the driving part restores to the initial position and is not connected with the first part and the second part at the same time.
Optionally, in a process that the accelerator driving claw drives the accelerator rod to reciprocate in a preset track, the thickness of the connecting portion is smaller than the sum of the heights of the first portion and the insulating member, or the thickness of the connecting portion is smaller than the sum of the heights of the second portion and the insulating member.
Optionally, the driving mechanism is a manipulator, the driving mechanism is connected with a force value measuring mechanism, and the force value measuring mechanism measures an action resistance value of the throttle lever in a running state to determine whether the throttle platform is qualified in installation.
The technical scheme of the invention has the following advantages:
1. the invention provides an automatic following measuring device for an automatic accelerator of an airplane, which comprises:
a throttle drive pawl, the throttle drive pawl comprising: the connecting part is connected with the driving mechanism, and the driving part is connected with the throttle lever in a matching way;
the jack catch linkage part is arranged on the throttle lever; the jaw linkage member includes: the throttle connecting part is used for connecting the throttle lever; the accommodating cavity is provided with: the first connecting surface is used for pulling the accelerator driving clamping jaw, and the second connecting surface is used for pushing the accelerator driving clamping jaw; the accommodating cavity is also provided with a sliding space for the driving part to slide in the accommodating cavity so as to be separately connected with the first connecting surface or the second connecting surface;
the follow-releasing driving mechanism is used for driving the first connecting surface or the second connecting surface to be far away from the driving part so as to release the automatic follow of the aircraft accelerator;
and the measuring mechanism is used for measuring whether the aircraft accelerator releases the automatic following or not and recording the driving force value applied to the first connecting surface or the second connecting surface by the following releasing driving mechanism when the automatic following is released.
In the invention, the accommodating cavity is internally provided with the accommodating space for the driving part to slide, so that the throttle lever can pull the driving part through the first connecting surface of the clamping jaw linkage part, and the clamping jaw linkage part can follow the automatic following action of the throttle lever. In addition, the throttle lever can push the driving part through the second connecting surface of the jaw linkage component, and the jaw linkage component can follow the automatic following action of the throttle lever. In the automatic following process, the following-releasing driving mechanism can drive the driving part to be far away from the first connecting surface or the second connecting surface so as to release the automatic following of the airplane accelerator. In the process that the follow-up removing driving mechanism drives the driving part, the measuring mechanism can measure whether the automatic follow-up of the aircraft accelerator is removed or not, and records the driving force value applied to the first connecting surface or the second connecting surface by the follow-up removing driving mechanism when the automatic follow-up is removed, so that the measurement work of measuring the driving force required by the conversion from the automatic cruise to the manual control of the aircraft accelerator push rod is realized.
2. The cross section of the accelerator driving clamping jaw is of an I-shaped structure, and the accommodating cavity is provided with an opening into which the accelerator driving clamping jaw is inserted.
According to the invention, the accelerator driving clamping jaw is arranged in an I-shaped structure, so that the accelerator driving clamping jaw can effectively and conveniently drive the accelerator rod to release automatic cruising through the clamping jaw linkage component. The throttle driving clamping jaw with the I-shaped structure can reduce the linkage part of the throttle driving clamping jaw and the clamping jaw and remove the connection and fixation of the following driving mechanism.
3. The invention provides an automatic following measuring device for an automatic throttle of an airplane, wherein a following releasing driving mechanism comprises: a first push rod and a second push rod; the first push rod is in driving contact with the first connecting surface under the condition that the claw linkage component pulls the accelerator to drive the claws, and the first connecting surface of the accommodating cavity is driven to be far away from the driving part; and under the condition that the claw linkage part pushes the throttle rod, the second push rod is in driving contact with the second connecting surface, and the second connecting surface of the accommodating cavity is driven to be far away from the driving part.
In the invention, the first connecting surface of the accommodating cavity is driven to be far away from the driving part by the first push rod, so that the automatic following state of the throttle lever can be effectively released, and the driving force required by the conversion from automatic cruise to manual control of the accelerator push rod of the airplane can be measured by measuring the thrust value generated by the first push rod. Or the second push rod drives the first connecting surface of the accommodating cavity to be far away from the driving part, so that the automatic following state of the throttle lever can be effectively released, and the driving force required by the conversion from automatic cruise to manual control of the accelerator push rod of the airplane is measured by measuring the thrust value generated by the first push rod. The first push rod and the second push rod can be electric push rods or hydraulic push rods.
4. The invention provides an automatic following measuring device for an automatic accelerator of an airplane, which is characterized in that two first push rods are arranged on a driving part and symmetrically arranged at two sides of an opening; and/or the number of the second push rods is two, the second push rods are arranged on the driving part and symmetrically arranged on two sides of the opening.
An automatic following measuring device for an aircraft auto throttle, further comprising: and the push rod controller is in communication connection with the first push rod and the second push rod respectively and is used for controlling the telescopic action of the first push rod and the telescopic action of the second push rod respectively and independently. The user controls the first push rod and the second push rod to independently act through the push rod controller, so that the driving part restores the initial position and is not connected with the first part and the second part at the same time.
In the invention, the telescopic length of one of the two first push rods arranged on the same side or the telescopic length of one of the two second push rods can be respectively adjusted by an operator according to the requirement through the push rod controller, so that the driving part is corrected from the inclined position to the normal position, and further the preparation is made for the next measurement.
5. According to the automatic following measuring device for the automatic throttle of the airplane, provided by the invention, the first connecting surface and the second connecting surface are respectively provided with the first electromagnetic mechanism and the second electromagnetic mechanism, and the driving part is a magnetic part with the magnetism opposite to that of the first electromagnetic mechanism and the second electromagnetic mechanism;
the first electromagnetic mechanism is controlled to generate a magnetic field to apply a first magnetic force towards the driving part to make the first magnetic force far away from the first connecting surface, and the first connecting surface of the accommodating cavity is driven to far away from the driving part;
the second electromagnetic mechanism is controlled to generate a magnetic field to apply a first magnetic field force to the driving portion to enable the driving portion to be far away from the second connecting surface, and the second connecting surface of the accommodating cavity is driven to be far away from the driving portion.
In the present invention, the first electromagnetic mechanism and the first electromagnetic mechanism generate a magnetic field force, thereby driving the driving portion away from the first connection surface or the second connection surface. The size of the magnetic field force is calculated by monitoring the size of the magnetic field, so that the measurement difficulty of measuring the driving force of the pushing driving part is effectively reduced, and the measurement accuracy is improved.
6. The invention provides an automatic following measuring device for an automatic throttle of an airplane, which comprises a measuring mechanism and a measuring mechanism, wherein the measuring mechanism comprises: the driving force sensor is arranged on the follow-up releasing driving mechanism and used for measuring a driving force value generated by the follow-up releasing driving mechanism; the accelerator lever driving force sensor is arranged on the accelerator lever and used for detecting a driving force value generated by the accelerator lever, and when the driving force of the accelerator lever is reduced to zero, the automatic following of the airplane accelerator is removed.
In the present invention, it is determined whether the automatic following state is released by the aircraft throttle system by measuring the driving force of the throttle stick. When the automatic following state is released, the driving force of the accelerator lever to the jaw linkage part and the accelerator driving jaw is zero.
7. The invention provides an automatic following measuring device for an automatic throttle of an airplane, which comprises a measuring mechanism and a measuring mechanism, wherein the measuring mechanism comprises: the driving force sensor is arranged on the follow-up releasing driving mechanism and used for measuring a driving force value generated by the follow-up releasing driving mechanism; and the accelerator lever direction sensor is arranged on the accelerator lever and used for detecting the moving direction of the accelerator lever, and when the moving direction of the accelerator lever is opposite to the automatic following direction of the accelerator lever, the airplane accelerator is relieved from automatic following.
In the invention, when the moving direction of the throttle lever is opposite to the automatic following of the throttle lever, the throttle system can automatically release the automatic following state. At the moment, the driving force generated by the follow-up releasing driving mechanism measured by the driving force sensor is the driving force value for releasing the automatic follow-up of the airplane accelerator.
8. The invention provides an automatic following measuring device for an automatic accelerator of an airplane,
the accommodation chamber includes: a first portion and a second portion connected together by an insulator; the first part and the second part are both made of conductive materials; a rotating gap for the driving part to rotate is formed between the driving part and the inner cavity wall of the accommodating cavity and is close to one side of the insulating part;
the automatic following measuring device for the aircraft automatic throttle further comprises: a circuit detection mechanism; the circuit detection mechanism includes: detection circuits connected to the first and second portions, respectively; when the accelerator driving claw is separated from the preset track, the driving part is respectively connected with the first part and the second part so as to enable the detection circuit to be conducted, and the driving mechanism controller controls the driving mechanism to stop acting.
In the present invention, the first part and the second part are connected together by an insulating member; the first part and the second part are both made of conductive materials and are connected together through a detection circuit.
When the accelerator drives the jaw to move along the preset track, the driving part positioned in the accommodating cavity is only attached and connected with one of the first part and the second part. The driving part can not incline in the accommodating cavity, and the detection circuit is not conducted at the moment. Position offset takes place when throttle drive jack catch, when throttle drive jack catch deviates on the glide plane at throttle pole place, perhaps throttle drive jack catch does not slide according to the radian of presetting the track, position slope can take place at the drive division of holding intracavity, thereby the drive division through above-mentioned electrically conductive material switches on first portion and second portion, detection circuitry can send signal for the actuating mechanism controller after being switched on, this actuating mechanism controller can control actuating mechanism stop motion, thereby prevent that whether qualified in-process of aircraft automatic throttle measuring mechanism's installation at the throttle platform from damaging the aircraft throttle system, cause great economic loss. Above-mentioned structure can realize effectively, follows the testing process in the automation, perhaps through throttle lever action resistance value under the running state and then judge whether qualified in-process of installation of throttle platform, guarantees effectively that throttle drive jack catch can in time stop throttle drive jack catch action when deviating the orbital radian of predetermineeing slides to avoid above-mentioned throttle drive jack catch to take place the problem of throttle lever damage.
9. According to the automatic following measuring device for the automatic throttle of the airplane, provided by the invention, in the process that the throttle driving claw drives the throttle rod to reciprocate in a preset track, the thickness of the connecting part is smaller than the sum of the heights of the first part and the insulating part, or the thickness of the connecting part is smaller than the sum of the heights of the second part and the insulating part.
In the present invention, the thickness of the connecting portion is set to be smaller than the sum of the heights of the first portion and the insulating member, or the thickness of the connecting portion is set to be smaller than the sum of the heights of the second portion and the insulating member. The accelerator driving claw can be effectively prevented from simultaneously contacting the first part and the second part which form the accommodating cavity when the accelerator driving claw does not have position deviation, and the driving mechanism controller is prevented from receiving an error signal to control the driving mechanism to stop acting.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic view of a connecting structure of an accommodating cavity of an automatic aircraft accelerator automatic following measuring device provided by the invention when an accelerator driving jaw is pulled by a first connecting surface;
FIG. 2 is a schematic diagram of the following releasing driving mechanism of the present invention, which pushes the driving portion away from the first connecting surface via the first push rod to release the automatic following of the aircraft throttle;
FIG. 3 is a schematic view of a connection structure when an accommodating cavity of the automatic accelerator automatic following measuring device of the airplane pushes an accelerator to drive a jaw through a second connection surface;
FIG. 4 is a schematic diagram of the following releasing driving mechanism provided by the present invention, which pushes the driving portion away from the second connecting surface via the second push rod to release the automatic following of the aircraft throttle;
FIG. 5 is a schematic structural diagram of an automatic follow-up measuring device with a circuit detection mechanism according to the present invention;
FIG. 6 is a schematic perspective view of a pawl linkage assembly with a follow-up release driving mechanism according to the present invention;
FIG. 7 is a schematic view of a three-dimensional structure of a jaw linkage component capable of stopping the operation of an accelerator driving jaw when the accelerator driving jaw slides in a radian deviating from a preset track according to the present invention;
FIG. 8 is a schematic view of a three-dimensional structure of a throttle driving jaw provided by the invention;
fig. 9 is a schematic perspective view of a driving mechanism according to the present invention.
Description of reference numerals:
1-the accelerator drives the jaw; 2-a drive mechanism; 3-a connecting part; 4-throttle lever; 5-a drive section; 6-an accommodating cavity; 7-a first connection face; 8-a second connection face; 9-opening; 10-a first push rod; 11-a second push rod; 12-an insulator; 13-a first part; 14-a second part; 15-rotational play; 16-a detection circuit; 17-a drive mechanism controller; 18-a first electromagnetic mechanism; 19-a second electromagnetic mechanism; 20-throttle connection.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Furthermore, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Example 1
An automatic following measuring device for an aircraft automatic throttle is described, as shown in fig. 1 and 3, comprising:
throttle drive dog 1, throttle drive dog 1 as shown in fig. 8 includes: a connecting part 3 connected with the driving mechanism 2 as shown in fig. 9, and a driving part 5 connected with the throttle lever 4 in a matching way;
a jaw linkage part as shown in fig. 6 provided on the throttle lever 4; the jaw linkage member includes: the throttle connecting part 20 is used for connecting the throttle lever 4 with the accommodating cavity 6 for accommodating the driving part 5; the accommodation chamber 6 has: a first connecting surface 7 for pulling the accelerator driving claw 1 and a second connecting surface 8 for pushing the accelerator driving claw 1; the accommodating cavity 6 is also internally provided with a sliding space for the driving part 5 to slide inside so as to be separately connected with the first connecting surface 7 or the second connecting surface 8 respectively;
the follow-releasing driving mechanism is used for driving the first connecting surface 7 or the second connecting surface 8 to be far away from the driving part 5 so as to release the automatic follow of the aircraft throttle; as shown in fig. 2 and 4, the release following drive mechanism includes: a first push rod 10 and a second push rod 11; when the jaw linkage component pulls the accelerator to drive the jaw 1, the first push rod 10 is in driving contact with the first connecting surface 7, and drives the first connecting surface 7 of the accommodating cavity 6 to be far away from the driving part 5; in addition, when the jaw linkage component pushes the throttle rod 4, the second push rod 11 is driven to abut against the second connecting surface 8, and drives the second connecting surface 8 of the accommodating cavity 6 to be far away from the driving part 5. The accommodating cavity 6 is driven by the first push rod 10 and the second push rod 11, so that the throttle lever 4 is pushed to remove the automatic follow-up of the automatic throttle of the airplane, and the structure has the advantages of stable and reliable structure, large driving force and easiness in measurement of the driving force;
and the measuring mechanism is used for measuring whether the automatic following of the accelerator of the airplane is released or not and recording the driving force value applied to the first connecting surface 7 or the second connecting surface 8 by the follow-releasing driving mechanism when the automatic following is released. The measuring mechanism includes: the driving force sensor is arranged on the follow-up releasing driving mechanism and used for measuring a driving force value generated by the follow-up releasing driving mechanism; and the accelerator lever driving force sensor is arranged on the accelerator lever 4 and used for detecting the driving force value generated by the accelerator lever 4, and when the driving force of the accelerator lever 4 is reduced to zero, the airplane accelerator is removed from automatic following.
In the present embodiment, as shown in fig. 1 to 4, the first push rods 10 are two and are disposed on the driving portion 5 and symmetrically disposed on two sides of the opening 9; the number of the second push rods 11 is two, and the second push rods are arranged on the driving part 5 and symmetrically arranged on two sides of the opening 9.
An automatic following measuring device for an aircraft auto throttle, further comprising:
the push rod controller is respectively in communication connection with the first push rod 10 and the second push rod 11;
the push rod controller is used for respectively controlling two first push rods 10 arranged on the same side of the accommodating cavity 6 to independently stretch and retract so that the driving part 5 is not inclined any more and is respectively connected with the first part 13 and the second part 14;
the push rod controller is used for respectively controlling two second push rods 11 arranged on the same side of the accommodating cavity 6 to independently extend and retract so that the driving part 5 is not inclined any more and is respectively connected with the first part 13 and the second part 14.
In the invention, the push rod controller can enable an operator to respectively adjust the telescopic length of one first push rod 10 of the two first push rods 10 arranged on the same side or the telescopic length of one second push rod 11 of the two second push rods 11 according to requirements, so that the driving part 5 is corrected from an inclined position to a normal position, and further the next measurement is prepared.
In this embodiment, as shown in fig. 1, the cross section of the accelerator driving claw 1 is an i-shaped structure, and the accommodating cavity 6 is provided with an opening 9 into which the accelerator driving claw 1 is inserted. The accelerator driving clamping jaw 1 is arranged to be of an I-shaped structure, so that the accelerator driving clamping jaw 1 can effectively and conveniently drive the accelerator rod 4 to release automatic cruising through the clamping jaw linkage component. The throttle driving clamping jaw 1 with the I-shaped structure can reduce the linkage part of the throttle driving clamping jaw 1 and the clamping jaw and remove the connection and fixation of the following driving mechanism.
Of course, the present embodiment does not specifically limit the specific structure of the measuring mechanism, and in other embodiments, the measuring mechanism includes: the driving force sensor is arranged on the follow-up releasing driving mechanism and used for measuring a driving force value generated by the follow-up releasing driving mechanism; and the accelerator lever direction sensor is arranged on the accelerator lever 4 and used for detecting the moving direction of the accelerator lever 4, and when the moving direction of the accelerator lever 4 is opposite to the automatic following of the accelerator lever 4, the automatic following of the airplane accelerator is removed.
Of course, the specific structure of the measuring mechanism is not specifically limited in this embodiment, in other embodiments, the driving mechanism 2 is a manipulator, the driving mechanism 2 is connected to a force value measuring mechanism, and the force value measuring mechanism measures the motion resistance value of the throttle lever 4 in the operating state to determine whether the installation of the throttle table is qualified.
Example 2
An automatic following measuring device for an aircraft automatic throttle is described, as shown in fig. 1 and 3, comprising:
throttle drive jack catch 1, throttle drive jack catch 1 includes: a connecting part 3 connected with the driving mechanism 2, and a driving part 5 matched and connected with the throttle lever 4;
the jack catch linkage part is arranged on the throttle rod 4; the jaw linkage part includes: the throttle connecting part 20 is used for connecting the throttle lever 4 with the containing cavity 6 used for containing the driving part 5; the accommodation chamber 6 has: a first connecting surface 7 for pulling the accelerator driving claw 1 and a second connecting surface 8 for pushing the accelerator driving claw 1; the accommodating cavity 6 is also internally provided with a sliding space for the driving part 5 to slide inside so as to be separately connected with the first connecting surface 7 or the second connecting surface 8 respectively;
the follow-releasing driving mechanism is used for driving the first connecting surface 7 or the second connecting surface 8 to be far away from the driving part 5 so as to release the automatic follow of the aircraft throttle; and the measuring mechanism is used for measuring whether the aircraft accelerator releases the automatic following or not and recording the driving force value applied to the first connecting surface 7 or the second connecting surface 8 by the follow-releasing driving mechanism when the automatic following is released.
In the present embodiment, as shown in fig. 5, the release following drive mechanism includes: a first electromagnetic mechanism 18 and a second electromagnetic mechanism 19 respectively provided on the first connection face 7 and the second connection face 8;
the driving section 5 is a magnetic member magnetically opposite to the first electromagnetic mechanism 18 and the second electromagnetic mechanism 19;
the first electromagnetic mechanism 18 is controlled to generate a magnetic field to apply a first magnetic force towards the driving part 5 away from the first connection face 7, driving the first connection face 7 of the receiving cavity 6 away from the driving part 5;
the second electromagnetic means 19 are controlled to generate a magnetic field to apply a first magnetic force towards the driving portion 5 away from the second connection face 8, driving the second connection face 8 of the receiving cavity 6 away from the driving portion 5.
In the present embodiment, as shown in fig. 5 and 7, the accommodating chamber 6 includes: a first portion 13 and a second portion 14 connected together by an insulator 12; the first part 13 and the second part 14 are both made of conductive materials; a rotating gap 15 for the driving part 5 to rotate is arranged between the driving part 5 and the inner cavity wall of the accommodating cavity 6 and is close to one side of the insulating part 12; in the process that the throttle driving claw 1 drives the throttle rod 4 to reciprocate in a preset track, the thickness of the connecting part 3 is smaller than the sum of the heights of the first part 13 and the insulating part 12, or the thickness of the connecting part 3 is smaller than the sum of the heights of the second part 14 and the insulating part 12;
the automatic following measuring device for the aircraft automatic throttle further comprises: a circuit detection mechanism; the circuit detection mechanism includes: a detection circuit 16 connected to said first portion 13 and said second portion 14, respectively; when the accelerator driving claw 1 is separated from the preset track, the driving part 5 is respectively connected with the first part 13 and the second part 14 so as to enable the detection circuit 16 to be conducted, and the driving mechanism controller 17 controls the driving mechanism 2 to stop operating.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications derived therefrom are intended to be within the scope of the invention.
Claims (11)
1. An automatic following measuring device for an aircraft auto throttle, comprising:
throttle drive jack catch (1), throttle drive jack catch (1) includes: the connecting part (3) is connected with the driving mechanism (2), and the driving part (5) is matched and connected with the throttle lever (4);
the jaw linkage part is arranged on the throttle lever (4); the jaw linkage part includes: the throttle connecting part (20) is used for connecting the throttle lever (4); the accommodating chamber (6) has: a first connecting surface (7) used for pulling the accelerator driving claw (1) and a second connecting surface (8) used for pushing the accelerator driving claw (1); the accommodating cavity (6) is also internally provided with a sliding space for the driving part (5) to slide so as to be separately connected with the first connecting surface (7) or the second connecting surface (8);
the follow-releasing driving mechanism is used for driving the first connecting surface (7) or the second connecting surface (8) to be far away from the driving part (5) so as to release the automatic follow of the aircraft throttle;
and the measuring mechanism is used for measuring whether the aircraft accelerator releases the automatic following or not and recording the driving force value applied to the first connecting surface (7) or the second connecting surface (8) by the following releasing driving mechanism when the automatic following is released.
2. The automatic following measuring device for the automatic accelerator of an airplane according to claim 1, wherein the cross section of the accelerator driving claw (1) is of an i-shaped structure, and an opening (9) for inserting the accelerator driving claw (1) into the accommodating cavity (6) is formed in the accommodating cavity.
3. The automatic follow-up measuring device for an aircraft auto-throttle of claim 2, wherein the de-follow drive mechanism comprises: a first push rod (10) and a second push rod (11);
when the jaw linkage component pulls the accelerator to drive the jaw (1), the first push rod (10) is in driving contact with the first connecting surface (7) to drive the first connecting surface (7) of the accommodating cavity (6) to be far away from the driving part (5);
under the jack catch linkage part pushes the throttle lever (4), the second push rod (11) is in driving connection with the second connecting surface (8) in a butting mode, and drives the second connecting surface (8) of the accommodating cavity (6) to be far away from the driving part (5).
4. The automatic follow-up measuring device for an aircraft auto throttle according to claim 3,
the number of the first push rods (10) is two, the first push rods are arranged on the driving part (5) and are symmetrically arranged on two sides of the opening (9); and/or the presence of a gas in the gas,
the number of the second push rods (11) is two, and the second push rods are arranged on the driving portion (5) and symmetrically arranged on two sides of the opening (9).
5. The automatic follow-up measuring device for an aircraft auto throttle according to claim 1, characterized in that the follow-up release driving mechanism comprises: a first electromagnetic mechanism (18) and a second electromagnetic mechanism (19) arranged on the first connection face (7) and the second connection face (8), respectively;
the drive section (5) is a magnetic member magnetically opposite to the first electromagnetic mechanism (18) and the second electromagnetic mechanism (19);
-said first electromagnetic means (18) are controlled to generate a magnetic field to exert a first magnetic force towards said driving portion (5) away from said first connection face (7), driving said first connection face (7) of said housing cavity (6) away from said driving portion (5);
the second electromagnetic mechanism (19) is controlled to generate a magnetic field to apply a first magnetic force towards the drive portion (5) away from the second connection face (8), driving the second connection face (8) of the accommodation cavity (6) away from the drive portion (5).
6. The automatic follow-up measuring device for an aircraft auto-throttle according to any one of claims 1 to 5, characterized in that the measuring mechanism comprises:
the driving force sensor is arranged on the follow-up releasing driving mechanism and used for measuring a driving force value generated by the follow-up releasing driving mechanism;
the accelerator lever driving force sensor is arranged on the accelerator lever (4) and used for detecting a driving force value generated by the accelerator lever (4), and when the driving force of the accelerator lever (4) is reduced to zero, the airplane accelerator is removed from automatic following.
7. The automatic follow-up measuring device for an aircraft auto-throttle according to any one of claims 1 to 5, characterized in that the measuring mechanism comprises:
the driving force sensor is arranged on the follow-up releasing driving mechanism and used for measuring a driving force value generated by the follow-up releasing driving mechanism;
the accelerator lever direction sensor is arranged on the accelerator lever (4) and used for detecting the moving direction of the accelerator lever (4), and when the moving direction of the accelerator lever (4) is opposite to the automatic following of the accelerator lever (4), the airplane accelerator is relieved from automatic following.
8. The automatic following measuring device for aircraft autothrottles according to claim 4, characterized in that said housing chamber (6) comprises: a first portion (13) and a second portion (14) connected together by an insulator (12); the first part (13) and the second part (14) are both made of conductive materials; a rotating gap (15) for the driving part (5) to rotate is arranged between the driving part (5) close to one side of the insulating part (12) and the inner cavity wall of the accommodating cavity (6);
the automatic following measuring device for the aircraft automatic throttle further comprises: a circuit detection mechanism; the circuit detection mechanism includes: -a detection circuit (16) connected to said first portion (13) and to said second portion (14), respectively; when the accelerator driving claw (1) is separated from a preset track, the driving part (5) is respectively connected with the first part (13) and the second part (14) so as to enable the detection circuit (16) to be conducted, and the driving mechanism controller (17) controls the driving mechanism (2) to stop acting.
9. The automatic follow-up measuring device for an aircraft auto-throttle of claim 8, further comprising:
the push rod controller is respectively in communication connection with the first push rod (10) and the second push rod (11);
the push rod controller is used for respectively controlling two first push rods (10) arranged on the same side of the accommodating cavity (6) to independently extend and retract so that the driving part (5) does not incline any more and is respectively connected with the first part (13) and the second part (14); and/or the presence of a gas in the gas,
the push rod controller is used for respectively controlling two second push rods (11) arranged on the same side of the accommodating cavity (6) to independently stretch and retract so that the driving part (5) does not incline any more and is respectively connected with the first part (13) and the second part (14).
10. The automatic follow-up measuring device for the aircraft auto throttle according to claim 8, characterized in that the thickness of the connecting portion (3) is less than the sum of the heights of the first portion (13) and the insulating member (12) or the thickness of the connecting portion (3) is less than the sum of the heights of the second portion (14) and the insulating member (12) during the reciprocating movement of the throttle lever (4) driven by the throttle driving pawl (1) in a preset orbit.
11. The automatic follow-up measuring device for an aircraft auto throttle according to claim 1,
the driving mechanism (2) is a mechanical arm, the driving mechanism (2) is connected with a force value measuring mechanism, and the force value measuring mechanism measures the action resistance value of the throttle lever (4) in the running state so as to judge whether the throttle platform is qualified or not.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210960424.7A CN115057002B (en) | 2022-08-11 | 2022-08-11 | Automatic following measuring device for automatic accelerator of airplane |
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| CN202210960424.7A CN115057002B (en) | 2022-08-11 | 2022-08-11 | Automatic following measuring device for automatic accelerator of airplane |
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| CN115057002B true CN115057002B (en) | 2022-11-01 |
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| CN116153167B (en) * | 2023-04-10 | 2023-08-22 | 北京天翼创展航空科技有限公司 | Flight simulator accelerator table follow-up device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB815003A (en) * | 1955-09-22 | 1959-06-17 | Bendix Aviat Corp | Thrust control for aircraft |
| CN105810041B (en) * | 2016-05-27 | 2019-06-25 | 徐舒青 | It is a kind of for simulating the device of airplane throttle control system |
| CN207850301U (en) * | 2017-12-18 | 2018-09-11 | 长春盖尔瑞孚艾斯曼汽车零部件有限公司 | A kind of semi-automatic detection device of automatic transmission handle button force and shift lever lifting stroke |
| CN109185442A (en) * | 2018-11-14 | 2019-01-11 | 合肥威艾尔智能技术有限公司 | A kind of auto-manual gearshift of driving simulator |
| CN110758750B (en) * | 2019-11-25 | 2021-05-18 | 华中科技大学 | Transmission mechanism for manual and automatic switching of airplane accelerator |
| CN112319848B (en) * | 2020-11-24 | 2021-06-08 | 北京天创凯睿科技有限公司 | Aircraft accelerator lever testing arrangement |
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