CN114228978A - Airplane control system with balancing mechanism - Google Patents
Airplane control system with balancing mechanism Download PDFInfo
- Publication number
- CN114228978A CN114228978A CN202111614584.8A CN202111614584A CN114228978A CN 114228978 A CN114228978 A CN 114228978A CN 202111614584 A CN202111614584 A CN 202111614584A CN 114228978 A CN114228978 A CN 114228978A
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- Prior art keywords
- balancing
- worm
- rocker arm
- flexible shaft
- trim
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
Abstract
The application belongs to the field of design of aircraft control systems, and particularly relates to an aircraft control system with a balancing mechanism. The method comprises the following steps: the device comprises a main driving control device, a secondary driving control device, a left side balancing execution mechanism, a right side balancing execution mechanism, a balancing motor and a linkage pull rod. The main driving control device is provided with a first load mechanism and a first rocker arm; the copilot operating device is provided with a second load mechanism and a second rocker arm; the first end of the left balancing executing mechanism is connected with the fixed end of the first loading mechanism, and the second end of the left balancing executing mechanism is connected with the first end of the left flexible shaft; the first end of the right balancing executing mechanism is connected with the fixed end of the second loading mechanism, and the second end of the right balancing executing mechanism is connected with the first end of the right flexible shaft; the balancing motor is provided with a left output shaft and a right output shaft, the left output shaft is connected with the second end of the left flexible shaft, and the right output shaft is connected with the second end of the right flexible shaft; the first end of the linkage pull rod is connected with the first rocker arm, and the second end of the linkage pull rod is connected with the second rocker arm.
Description
Technical Field
The application belongs to the field of design of aircraft control systems, and particularly relates to an aircraft control system with a balancing mechanism.
Background
In the airplane control system with double control systems, in order to meet the requirement of inter-channel control independence, a transverse linkage pull rod between a main driving control device and a secondary driving control device needs to be arranged on a longitudinal rotating shaft, and for the design scheme with a transverse balancing mechanism, a balancing linkage line system and a control linkage line system cannot be arranged on the longitudinal rotating shaft at the same time.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide an aircraft maneuvering system with a trim mechanism to address at least one problem with the prior art.
The technical scheme of the application is as follows:
an aircraft handling system with a trim mechanism, comprising:
a primary steering control device configured with a first load mechanism and a first rocker arm;
a secondary steering device provided with a second load mechanism and a second rocker arm;
the first end of the left balancing executing mechanism is connected with the fixed end of the first loading mechanism, and the second end of the left balancing executing mechanism is connected with the first end of the left flexible shaft;
the first end of the right-side balancing executing mechanism is connected with the fixed end of the second loading mechanism, and the second end of the right-side balancing executing mechanism is connected with the first end of the right-side flexible shaft;
the balancing motor is provided with a left output shaft and a right output shaft, the left output shaft is connected with the second end of the left flexible shaft, and the right output shaft is connected with the second end of the right flexible shaft;
and the first end of the linkage pull rod is connected with the first rocker arm, and the second end of the linkage pull rod is connected with the second rocker arm.
In at least one embodiment of the present application, the primary driving operation device is a primary steering column operation mechanism, and the first load mechanism is a spring.
In at least one embodiment of the present application, the copilot steering device is a copilot column steering mechanism and the second load mechanism is a spring.
In at least one embodiment of the present application, the left trim actuator includes a left housing, a left worm gear, and a third rocker arm, wherein,
the left worm is arranged in the left shell, and one end of the left worm is connected with the first end of the left flexible shaft;
the left worm wheel is connected with the spiral teeth of the left worm in a matching way;
one end of the third rocker arm is connected with the left worm wheel through a shared rotating shaft, and the other end of the third rocker arm is connected with the fixed end of the first load mechanism.
In at least one embodiment of the present application, the right trim actuator includes a right housing, a right worm gear, and a fourth rocker arm, wherein,
the right worm is arranged in the right shell, and one end of the right worm is connected with the first end of the right flexible shaft;
the right worm wheel is connected with the helical teeth of the right worm in a matching way;
one end of the fourth rocker arm is connected with the right worm wheel through a shared rotating shaft, and the other end of the fourth rocker arm is connected with the fixed end of the second load mechanism.
The invention has at least the following beneficial technical effects:
the aircraft control system with the balancing mechanism solves the problem that a balancing linkage line system and a control linkage line system cannot be coaxial by arranging the balancing mechanism connected by a flexible shaft between a main pilot control device and a copilot control device, realizes the function of balancing control force, reduces the control load of pilots, and improves the control comfort.
Drawings
FIG. 1 is a schematic illustration of an aircraft handling system with a trim mechanism according to an embodiment of the present application;
FIG. 2 is a schematic view of a left side trim actuator according to one embodiment of the present application;
FIG. 3 is a schematic view of a right side trim actuator according to one embodiment of the present application.
Wherein:
1-a primary driving steering device; 2-left trim actuator; 201-left side housing; 202-left worm; 203-left worm gear; 204-a third rocker arm; 3-a left flexible shaft; 4-a trim motor; 5-a right flexible shaft; 6-right trim actuator; 601-right side shell; 602-right worm; 603-right worm gear; 604-a fourth rocker arm; 7-copilot steering; 8-linkage pull rod.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 3.
The application provides an aircraft control system with trim mechanism, includes: the main driving control device 1, the auxiliary driving control device 7, the left side balancing execution mechanism 2, the right side balancing execution mechanism 6, the balancing motor 4 and the linkage pull rod 8.
Specifically, as shown in fig. 1, the main driving operation device 1 is provided with a first load mechanism and a first swing arm; the secondary operation device 7 is provided with a second load mechanism and a second rocker arm; the first end of the left balancing executing mechanism 2 is connected with the fixed end of the first loading mechanism, and the second end of the left balancing executing mechanism is connected with the first end of the left flexible shaft 3; the first end of the right balancing executing mechanism 6 is connected with the fixed end of the second loading mechanism, and the second end of the right balancing executing mechanism is connected with the first end of the right flexible shaft 5; the balancing motor 4 is provided with a left output shaft and a right output shaft, the left output shaft is connected with the second end of the left flexible shaft 3, and the right output shaft is connected with the second end of the right flexible shaft 5; the first end of the linkage pull rod 8 is connected with the first rocker arm, and the second end is connected with the second rocker arm.
In the dual-steering aircraft steering system according to the embodiment of the present application, the primary steering device 1 is a primary steering column steering mechanism, the first load mechanism is a spring, the secondary steering device 7 is a secondary steering column steering mechanism, and the second load mechanism is a spring.
In one embodiment of the present application, as shown in fig. 2-3, the left trim actuator 2 includes a left housing 201, a left worm 202, a left worm wheel 203, and a third rocker arm 204, wherein the left worm 202 is disposed in the left housing 201, and one end of the left worm 202 is connected to a first end of the left flexible shaft 3; the left worm wheel 203 is matched and connected with the helical teeth of the left worm 202; one end of the third rocker arm 204 is connected to the left worm wheel 203 via a common rotating shaft, and the other end is connected to the fixed end of the first load mechanism. In this embodiment, the right-side trim actuator 6 is the same as the left-side trim actuator 2, and includes a right-side housing 601, a right-side worm 602, a right-side worm wheel 603, and a fourth rocker arm 604, wherein the right-side worm 602 is disposed in the right-side housing 601, and one end of the right-side worm 602 is connected to the first end of the right-side flexible shaft 5; the right worm wheel 603 is in fit connection with the helical teeth of the right worm 602; one end of the fourth rocker arm 604 is connected with the right worm wheel 603 through a shared rotating shaft, the other end of the fourth rocker arm is connected with the fixed end of the second loading mechanism, and the rotating motion input by the flexible shaft is converted into the swinging motion output by the rocker arm through a worm and gear mechanism.
According to the airplane control system with the balancing mechanism, the output shaft of the balancing motor 4 is respectively connected with the left and right balancing executing mechanisms through the two flexible shafts, the left and right balancing executing mechanisms are respectively connected with the fixed ends of the load mechanisms in the main and auxiliary driving control devices, and the two ends of the linkage pull rod 8 are respectively connected with the rocker arms in the main and auxiliary driving control devices. The rotating motion of the output shaft of the balancing motor 4 drives the worm corresponding to the balancing executing mechanism through the flexible shafts on the left side and the right side, and then drives the rocker arm to swing through the worm gear mechanism, so that the fixed end of the load mechanism in the steering column control mechanism is pushed, the deformation of the spring of the load mechanism is reduced, and the control force is reduced or eliminated.
The aircraft control system with the balancing mechanism solves the problem that a balancing linkage line system and a control linkage line system cannot be coaxial by arranging the balancing mechanism connected by a flexible shaft between a main pilot control device and a copilot control device, realizes the function of balancing control force, reduces the control load of pilots, and improves the control comfort.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. An aircraft operating system with a trim mechanism, comprising:
a primary steering control device (1), said primary steering control device (1) being configured with a first load mechanism and a first rocker arm;
a copilot operating device (7), wherein the copilot operating device (7) is provided with a second load mechanism and a second rocker arm;
the first end of the left balancing executing mechanism (2) is connected with the fixed end of the first load mechanism, and the second end of the left balancing executing mechanism is connected with the first end of the left flexible shaft (3);
the first end of the right-side balancing executing mechanism (6) is connected with the fixed end of the second load mechanism, and the second end of the right-side balancing executing mechanism (6) is connected with the first end of the right-side flexible shaft (5);
the balancing motor (4) is provided with a left output shaft and a right output shaft, the left output shaft is connected with the second end of the left flexible shaft (3), and the right output shaft is connected with the second end of the right flexible shaft (5);
the linkage pull rod (8), the first end of linkage pull rod (8) with first rocking arm is connected, the second end with the second rocking arm is connected.
2. Aircraft handling system with trim according to claim 1, characterized in that the primary steering handling device (1) is a primary pilot column handling mechanism and the first load means is a spring.
3. Aircraft handling system with trim according to claim 2, characterised in that the copilot handling device (7) is a copilot column handling and the second load means is a spring.
4. Aircraft handling system with trim arrangement according to claim 1, characterised in that the left-hand trim actuator (2) comprises a left-hand housing (201), a left-hand worm (202), a left-hand worm wheel (203) and a third rocker arm (204), wherein,
the left worm (202) is arranged in the left shell (201), and one end of the left worm (202) is connected with the first end of the left flexible shaft (3);
the left worm wheel (203) is in fit connection with the helical teeth of the left worm (202);
one end of the third rocker arm (204) is connected with the left worm wheel (203) through a shared rotating shaft, and the other end of the third rocker arm is connected with the fixed end of the first load mechanism.
5. The aircraft steering system with trim mechanism of claim 4, characterized in that the right trim actuator (6) comprises a right housing (601), a right worm (602), a right worm gear (603), and a fourth swing arm (604), wherein,
the right worm (602) is arranged in the right shell (601), and one end of the right worm (602) is connected with the first end of the right flexible shaft (5);
the right worm wheel (603) is in fit connection with the helical teeth of the right worm (602);
one end of the fourth rocker arm (604) is connected with the right worm wheel (603) through a shared rotating shaft, and the other end of the fourth rocker arm is connected with the fixed end of the second load mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111614584.8A CN114228978A (en) | 2021-12-27 | 2021-12-27 | Airplane control system with balancing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111614584.8A CN114228978A (en) | 2021-12-27 | 2021-12-27 | Airplane control system with balancing mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN114228978A true CN114228978A (en) | 2022-03-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111614584.8A Pending CN114228978A (en) | 2021-12-27 | 2021-12-27 | Airplane control system with balancing mechanism |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009060327A1 (en) * | 2009-12-23 | 2011-06-30 | Airbus Operations GmbH, 21129 | Airplane with a control device |
| CN103207064A (en) * | 2012-12-06 | 2013-07-17 | 中国人民解放军海军航空工程学院青岛校区 | In-situ testing system for flight control system loading mechanism |
| CN204832969U (en) * | 2015-08-11 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | Automatic every single move trimming system |
| CN109613927A (en) * | 2018-11-02 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | Mechanical manoeuvring system influences aircraft balanced to determine method under aircraft flexible deformation |
| CN112727902A (en) * | 2020-12-25 | 2021-04-30 | 兰州飞行控制有限责任公司 | Balancing mechanism and method for flexible connecting assembly transmission |
-
2021
- 2021-12-27 CN CN202111614584.8A patent/CN114228978A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009060327A1 (en) * | 2009-12-23 | 2011-06-30 | Airbus Operations GmbH, 21129 | Airplane with a control device |
| CN103207064A (en) * | 2012-12-06 | 2013-07-17 | 中国人民解放军海军航空工程学院青岛校区 | In-situ testing system for flight control system loading mechanism |
| CN204832969U (en) * | 2015-08-11 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | Automatic every single move trimming system |
| CN109613927A (en) * | 2018-11-02 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | Mechanical manoeuvring system influences aircraft balanced to determine method under aircraft flexible deformation |
| CN112727902A (en) * | 2020-12-25 | 2021-04-30 | 兰州飞行控制有限责任公司 | Balancing mechanism and method for flexible connecting assembly transmission |
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Inventor after: Yu Jie Inventor after: Chen Xiantong Inventor after: Chen Shuai Inventor before: Yu Jie Inventor before: Chen Xiantong Inventor before: Chen Shuai Inventor before: Yin Yuji |
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