CN114313218A - Transmission mechanism of resistance rudder and aircraft - Google Patents
Transmission mechanism of resistance rudder and aircraft Download PDFInfo
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- CN114313218A CN114313218A CN202111573929.XA CN202111573929A CN114313218A CN 114313218 A CN114313218 A CN 114313218A CN 202111573929 A CN202111573929 A CN 202111573929A CN 114313218 A CN114313218 A CN 114313218A
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Abstract
The invention provides a transmission mechanism of a resistance rudder and an aircraft, wherein the transmission mechanism of the resistance rudder comprises: the upper rotating shaft and the lower rotating shaft are arranged at intervals and fixedly; one end of the upper resistance rudder is hinged with the upper rotating shaft, the other end of the upper resistance rudder can rotate around the upper rotating shaft, and the inner side of the upper resistance rudder is hinged with an upper driving rod; one end of the lower resistance rudder is hinged with the lower rotating shaft, the other end of the lower resistance rudder can rotate around the lower rotating shaft, and the inner side of the lower resistance rudder is hinged with a lower driving rod; the telescopic driving assembly, the upper driving rod and the lower driving rod are hinged to the telescopic driving assembly, and the telescopic driving assembly can drive the upper resistance rudder and the lower resistance rudder to synchronously expand or synchronously retract. The embodiment of the invention reduces one telescopic driving component and a corresponding rudder control system, thereby achieving the purposes of saving the installation space and improving the control efficiency.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a transmission mechanism of a resistance rudder and an aircraft.
Background
Conventional layout aircraft typically have rudders on the vertical tail for heading control. The tailless flying wing layout is an advanced aircraft layout design, is applied to military aircrafts at present, and is an important research direction of civil aircrafts. The flying wing layout eliminates the tail wing, and a split resistance rudder is usually arranged on an outer wing section to carry out course control.
The traditional split resistance rudder transmission mechanism adopts a method of respectively controlling two control surfaces, and two steering engines need to be arranged. And because the size of the control surface is limited, the driving force arm of the control surface is shorter, the transmission design is difficult, and a plurality of transmission mechanisms are arranged to protrude out of the appearance surface of the aircraft, so that the pneumatic and stealth performances are greatly reduced.
Disclosure of Invention
In view of this, embodiments of the present invention provide a transmission mechanism of a resistance rudder and an aircraft, so as to achieve the purposes of saving an installation space and improving control efficiency.
The embodiment of the specification provides the following technical scheme: a drag rudder transmission mechanism comprising: the upper rotating shaft and the lower rotating shaft are arranged at intervals and fixedly; one end of the upper resistance rudder is hinged with the upper rotating shaft, the other end of the upper resistance rudder can rotate around the upper rotating shaft, and the inner side of the upper resistance rudder is hinged with an upper driving rod; one end of the lower resistance rudder is hinged with the lower rotating shaft, the other end of the lower resistance rudder can rotate around the lower rotating shaft, and the inner side of the lower resistance rudder is hinged with a lower driving rod; the telescopic driving assembly, the upper driving rod and the lower driving rod are hinged to the telescopic driving assembly, and the telescopic driving assembly can drive the upper resistance rudder and the lower resistance rudder to synchronously expand or synchronously retract.
Further, flexible drive assembly includes driving machine body and telescopic link, and the driving machine body sets up in the outside of last resistance rudder and resistance rudder down, the one end and the driving machine body coupling of telescopic link, and the other end and the last actuating lever of telescopic link and actuating lever down are all articulated.
Furthermore, the transmission mechanism of the resistance rudder also comprises a fixedly arranged guide assembly, and one end of the telescopic rod penetrates through the guide assembly and is hinged with the upper driving rod and the lower driving rod.
Further, the guide assembly is a tubular structure, and both ends of the tubular structure are open ends.
Furthermore, a hinge point of the upper driving rod and the telescopic rod is a first hinge point, a hinge point of the upper driving rod and the upper resistance rudder is a second hinge point, and the distance between the first hinge point and the second hinge point is a first distance; the pin joint of lower actuating lever and telescopic link is the third pin joint point, and the pin joint of lower actuating lever and lower resistance rudder is the fourth pin joint, and the distance between third pin joint and the fourth pin joint is the second interval, and wherein, first interval equals the second interval.
Furthermore, a hinge point of the upper driving rod and the telescopic rod is a first hinge point, a hinge point of the upper driving rod and the upper resistance rudder is a second hinge point, and the distance between the first hinge point and the second hinge point is a first distance; the pin joint of lower actuating lever and telescopic link is the third pin joint point, and the pin joint of lower actuating lever and lower resistance rudder is the fourth pin joint, and the distance between third pin joint and the fourth pin joint is the second interval, and wherein, first interval is less than the second interval.
Furthermore, a hinge point of the upper driving rod and the telescopic rod is a first hinge point, a hinge point of the upper driving rod and the upper resistance rudder is a second hinge point, and the distance between the first hinge point and the second hinge point is a first distance; the pin joint of lower actuating lever and telescopic link is the third pin joint point, and the pin joint of lower actuating lever and lower resistance rudder is the fourth pin joint, and the distance between third pin joint and the fourth pin joint is the second interval, and wherein, first interval is greater than the second interval.
Furthermore, first pin joint, second pin joint, third pin joint point and fourth pin joint all adopt joint bearing to connect.
Further, the driving machine body is a steering engine or a hydraulic cylinder.
Further, the inside wall of going up the resistance rudder is provided with first recess, and the inside wall of resistance rudder is provided with the second recess down, and first recess corresponds with second recess position and can dock and form accommodation space, goes up the actuating lever and articulates in first recess, and the actuating lever is articulated in with the second recess down, and when the inside wall of last resistance rudder and the inside wall butt of resistance rudder down, the other end homoenergetic of going up actuating lever, actuating lever and telescopic link can be arranged in accommodation space.
Further, the transmission mechanism of the resistance rudder also comprises a fixing assembly which is hinged on the telescopic driving assembly and used for arranging the telescopic driving assembly on the setting component.
The invention also provides an aircraft which comprises a transmission mechanism of the resistance rudder and an aircraft body, wherein the transmission mechanism of the resistance rudder is the transmission mechanism of the resistance rudder, and an upper rotating shaft and a lower rotating shaft of the transmission mechanism of the resistance rudder are fixedly connected with the aircraft body.
Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise: compared with the prior art which is not improved, the telescopic driving assembly and the corresponding rudder control system are omitted, so that the purposes of saving the installation space and improving the control efficiency are achieved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
fig. 2 is a schematic diagram of an embodiment of the present invention.
1. An upper resistance rudder; 2. a lower resistance rudder; 3. an upper rotating shaft; 4. a lower rotating shaft; 5. an upper drive rod; 6. a lower drive rod; 7. a driver body; 8. a fixing assembly; 9. a guide assembly; 10. a telescopic rod.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. 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.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number and aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present application, and the drawings only show the components related to the present application rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
As shown in fig. 1, the embodiment of the present invention provides a transmission mechanism of a resistance rudder, which includes an upper rotating shaft 3, a lower rotating shaft 4, an upper resistance rudder 1, a lower resistance rudder 2 and a telescopic driving assembly. The upper rotating shaft 3 and the lower rotating shaft 4 are arranged at intervals and fixedly. Go up the one end of resistance rudder 1 and pivot 3 articulated on, go up the other end of resistance rudder 1 and can rotate around pivot 3 on, and the inboard articulated actuating lever 5 that is provided with of going up resistance rudder 1. One end of the lower resistance rudder 2 is hinged with the lower rotating shaft 4, the other end of the lower resistance rudder 2 can rotate around the lower rotating shaft 4, and the inner side of the lower resistance rudder 2 is hinged with a lower driving rod 6; the telescopic driving assembly, the upper driving rod 5 and the lower driving rod 6 are hinged with the telescopic driving assembly, and the telescopic driving assembly can drive the upper resistance rudder 1 and the lower resistance rudder 2 to synchronously unfold or synchronously retract.
Compared with the prior art which is not improved, the telescopic driving assembly and the corresponding rudder control system are reduced, so that the purposes of saving the installation space and improving the control efficiency are achieved.
It should be noted that, in an embodiment, the upper rotating shaft 3 and the lower rotating shaft 4 may be the same rotating shaft, so that the present solution can be further simplified.
The telescopic driving assembly comprises a driving machine body 7 and a telescopic rod 10, wherein the driving machine body 7 is arranged on the outer sides of an upper resistance rudder 1 and a lower resistance rudder 2, one end of the telescopic rod 10 is connected with the driving machine body 7, and the other end of the telescopic rod 10 is hinged to an upper driving rod 5 and a lower driving rod 6.
In the embodiment of the invention, the driving machine body 7 is a steering engine or a hydraulic cylinder, and when the driving machine works, the driving machine body 7 can drive the telescopic rod 10 to do linear telescopic motion, so that the upper driving rod 5 and the lower driving rod 6 are pushed to do motion, and the upper resistance rudder 1 and the lower resistance rudder 2 are synchronously unfolded or synchronously retracted.
According to the embodiment of the invention, the transmission mechanism is simplified, the driving machine body 7 is connected with the upper resistance rudder 1 and the lower resistance rudder 2 only through the telescopic rod 10, and compared with the technical scheme before improvement, related parts of the transmission link of the driving machine body 7 are fewer, so that the reliability of the embodiment can be further improved.
The transmission mechanism of the resistance rudder also comprises a fixedly arranged guide assembly 9, and one end of a telescopic rod 10 penetrates through the guide assembly 9 and is hinged with the upper driving rod 5 and the lower driving rod 6. The guide assembly 9 of the embodiment of the invention is of a cylindrical structure, and both ends of the cylindrical structure are open ends.
The guiding assembly 9 is generally fixed to the body structure and can guide the telescopic rod 10 so that the telescopic rod 10 can only move in a fixed direction. And the upper resistance rudder 1 and the lower resistance rudder 2 move symmetrically under the limit of the guide assembly 9. If the pneumatic loads of the upper resistance rudder 1 and the lower resistance rudder 2 are temporarily asymmetric, the guide assembly 9 provides a support reaction force to counteract the influence of the asymmetric loads. In an embodiment of the present invention, a linear bearing may be used as the guide assembly 9.
Of course, the guiding assembly 9 may be adjusted according to different requirements, for example, a limiting strip for circumferential rotation limiting is disposed on an inner ring of the guiding assembly 9, and a limiting groove for matching with the limiting strip is disposed on the outer periphery of the telescopic rod 10, so that the telescopic rod 10 can only achieve linear telescopic reciprocating motion and cannot rotate.
In an embodiment, not shown, the limit groove may be disposed on the inner ring of the guide assembly 9, and the limit protrusion may be disposed on the outer circumference of the telescopic rod 10.
In the embodiment of the invention, the hinge point of the upper driving rod 5 and the telescopic rod 10 is a first hinge point, the hinge point of the upper driving rod 5 and the upper resistance rudder 1 is a second hinge point, and the distance between the first hinge point and the second hinge point is a first distance; the pin joint of lower actuating lever 6 and telescopic link 10 is the third pin joint point, and the pin joint of lower actuating lever 6 and lower resistance rudder 2 is the fourth pin joint, and the distance between third pin joint point and the fourth pin joint is the second interval, and wherein, first interval equals the second interval.
In this embodiment, the first distance is equal to the second distance, that is, the acting lengths of the upper driving rod 5 and the lower driving rod 6 are the same, and the upper resistance rudder 1 and the lower resistance rudder 2 are symmetrically distributed, that is, the rudder angles of the upper resistance rudder 1 and the lower resistance rudder 2 are equal but opposite.
In an embodiment not shown, in the case where the aerodynamic loads of the upper and lower resistance rudders 1 and 2 are not symmetrical for a long time, the upper and lower resistance rudders 1 and 2 can also be asymmetrically moved by adjusting the lengths of the upper and lower drive rods 5 and 6. Even if the first pitch is smaller than the second pitch or the first pitch is made larger than the second pitch.
Preferably, the first hinge point, the second hinge point, the third hinge point and the fourth hinge point are all connected by joint bearings. The knuckle bearing is adopted as the connecting part of the hinge point, so that the problem of inconvenience in installation caused by installation errors can be avoided through the characteristics of the knuckle bearing, and normal assembly can be realized according to the embodiment of the invention.
Go up the inside wall of resistance rudder 1 and be provided with first recess, the inside wall of lower resistance rudder 2 is provided with the second recess, first recess corresponds with second recess position and can dock and form accommodation space, go up actuating lever 5 and articulate in first recess, in lower actuating lever 6 is articulated and the second recess, and when the inside wall of last resistance rudder 1 and the inside wall butt of lower resistance rudder 2, go up actuating lever 5, the other end homoenergetic of lower actuating lever 6 and telescopic link 10 can be arranged in accommodation space.
In the embodiment of the invention, the scheme that the first groove and the second groove are butted to form the accommodating space is adopted, and the transmission mechanisms can be arranged in the limited space, so that all the transmission mechanisms are positioned in the aerodynamic shape (arranged on the outer sides of the upper resistance rudder 1 and the lower resistance rudder 2 in the prior art), and the aerodynamic performance and the stealth performance of the whole machine are improved.
As shown in fig. 1, the transmission mechanism of the resistance rudder according to the embodiment of the present invention further includes a fixing member 8 which is hinge-coupled to the telescopic driving member and is used to fix the telescopic driving member to the setting member. The fixing assembly 8 is located at one side end part of the telescopic driving assembly far away from the upper resistance rudder 1 and the lower resistance rudder 2, and the position of the telescopic driving assembly can be adjusted conveniently by adopting a hinged connection mode, so that the mounting error is compensated, and the purpose of facilitating mounting is achieved.
Fig. 2 is a schematic diagram of an embodiment of the present invention, where a point a is a hinge point of the upper rotating shaft 3 and the upper resistance rudder 1, a point D is a hinge point of the upper driving rod 5 and the upper resistance rudder 1, a point C is a hinge point of the lower rotating shaft 4 and the lower resistance rudder 2, a point D is a hinge point of the lower driving rod 6 and the lower resistance rudder 2, a point E is a hinge point of the steering engine, the upper driving rod 5 and the lower driving rod 6, a point F is a fixed hinge point of the steering engine, and a point G is an auxiliary point convenient for calculation.
Analysis and calculation show that the steering engine driving force F satisfies the following formula (a):
the rudder exit angle δ of the upper resistance rudder 1 (or the lower resistance rudder 2) satisfies the following formula (b):
wherein the content of the first and second substances,
in the formula of gamma0The value of γ when the rudder exit angle δ is zero is shown, and M is the hinge moment of the upper resistance rudder 1 and the lower resistance rudder 2 (the hinge moment of the upper resistance rudder and the lower resistance rudder under the symmetric movement is equal, and the hinge moment is larger if the hinge moment is temporarily unequal). For a given embodiment of the method of the present invention,
γ0are all fixed values, and are all fixed values,
the change in (b) represents the extension or contraction of the telescopic rod 10 of the steering engine.
The relation between the steering engine driving force and the hinge moment of the upper resistance rudder 1 (or the lower resistance rudder 2) can be given when the steering engine telescopic rod 10 is in different elongation amounts through the formula (a). The rudder angle delta of the upper resistance rudder 1 (or the lower resistance rudder 2) and the elongation of the telescopic rod 10 can be given by the formula (b)
The relationship (2) of (c).
In some embodiments of the present invention, if it is found from the above formula that the driving force F of the driving machine body 7 or the rudder-out angle δ of the upper resistance rudder 1 (or the lower resistance rudder 2) cannot satisfy the requirement, the positions of the points a, B, E, etc. can be adjusted to make the formula in the above formula
The equivalence changes correspondingly, thereby adapting to the needs in practical use.
The analysis shows that the transmission mechanism of the resistance rudder has stronger designability, can adjust the positions of all hinge points according to the requirements of parameters such as transmission ratio, rudder output angle and the like in practical application, and can be finally matched with various practical application working conditions.
The embodiment of the invention also provides an aircraft, which comprises a transmission mechanism of the resistance rudder and an aircraft body, wherein the transmission mechanism of the resistance rudder is the transmission mechanism of the resistance rudder, and an upper rotating shaft 3 and a lower rotating shaft 4 of the transmission mechanism of the resistance rudder are fixedly connected with the aircraft body.
The embodiment of the invention has the following beneficial effects:
1. the two control surfaces of the split resistance rudder are controlled by one steering engine, so that one steering engine and a corresponding rudder control system are reduced, the installation space is saved, and the control efficiency is improved.
2. The technical scheme can utilize limited space to arrange the transmission mechanisms, and all the transmission mechanisms are positioned in the pneumatic appearance, so that the pneumatic performance and the stealth performance of the whole machine are improved.
3. The transmission mechanism is simplified, the steering engine output rod is connected with the control surface through the telescopic rod, the transmission links are fewer, and the reliability is further improved.
The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments can be referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for the method embodiments described later, since they correspond to the system, the description is simple, and for the relevant points, reference may be made to the partial description of the system embodiments.
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 (12)
1. A transmission mechanism for a resistance rudder, comprising:
an upper rotating shaft (3) and a lower rotating shaft (4) which are arranged at intervals and fixedly;
one end of the upper resistance rudder (1) is hinged with the upper rotating shaft (3), the other end of the upper resistance rudder (1) can rotate around the upper rotating shaft (3), and the inner side of the upper resistance rudder (1) is hinged with an upper driving rod (5);
one end of the lower resistance rudder (2) is hinged with the lower rotating shaft (4), the other end of the lower resistance rudder (2) can rotate around the lower rotating shaft (4), and the inner side of the lower resistance rudder (2) is hinged with a lower driving rod (6);
the telescopic driving assembly, upper driving pole (5) and lower driving pole (6) all with telescopic driving assembly is articulated, telescopic driving assembly can drive upper resistance rudder (1) and lower resistance rudder (2) and expand in step or withdraw the operation in step.
2. The transmission mechanism of the resistance rudder according to claim 1, wherein the telescopic driving assembly comprises a driving machine body (7) and a telescopic rod (10), the driving machine body (7) is arranged outside the upper resistance rudder (1) and the lower resistance rudder (2), one end of the telescopic rod (10) is connected with the driving machine body (7), and the other end of the telescopic rod (10) is hinged with both the upper driving rod (5) and the lower driving rod (6).
3. The transmission mechanism of the resistance rudder according to claim 2, characterized in that it further comprises a guide assembly (9) fixedly arranged, one end of the telescopic rod (10) passing through the guide assembly (9) and being hinged with the upper driving rod (5) and the lower driving rod (6).
4. The transmission of a resistance rudder according to claim 3, characterised in that the guide assembly (9) is of a cylindrical structure and both ends of the cylindrical structure are open ends.
5. The resistance rudder transmission mechanism according to claim 2,
a hinge point of the upper driving rod (5) and the telescopic rod (10) is a first hinge point, a hinge point of the upper driving rod (5) and the upper resistance rudder (1) is a second hinge point, and the distance between the first hinge point and the second hinge point is a first distance;
the hinge point of the lower driving rod (6) and the telescopic rod (10) is a third hinge point, the hinge point of the lower driving rod (6) and the lower resistance rudder (2) is a fourth hinge point, the distance between the third hinge point and the fourth hinge point is a second distance, and the first distance is equal to the second distance.
6. The resistance rudder transmission mechanism according to claim 2,
a hinge point of the upper driving rod (5) and the telescopic rod (10) is a first hinge point, a hinge point of the upper driving rod (5) and the upper resistance rudder (1) is a second hinge point, and the distance between the first hinge point and the second hinge point is a first distance;
the hinge point of the lower driving rod (6) and the telescopic rod (10) is a third hinge point, the hinge point of the lower driving rod (6) and the lower resistance rudder (2) is a fourth hinge point, the distance between the third hinge point and the fourth hinge point is a second distance, and the first distance is smaller than the second distance.
7. The resistance rudder transmission mechanism according to claim 2,
a hinge point of the upper driving rod (5) and the telescopic rod (10) is a first hinge point, a hinge point of the upper driving rod (5) and the upper resistance rudder (1) is a second hinge point, and the distance between the first hinge point and the second hinge point is a first distance;
the hinge point of the lower driving rod (6) and the telescopic rod (10) is a third hinge point, the hinge point of the lower driving rod (6) and the lower resistance rudder (2) is a fourth hinge point, the distance between the third hinge point and the fourth hinge point is a second distance, and the first distance is larger than the second distance.
8. The resistance rudder transmission mechanism according to any one of claims 5 to 7, wherein the first hinge point, the second hinge point, the third hinge point, and the fourth hinge point are connected with a joint bearing.
9. The transmission mechanism of the resistance rudder according to claim 2, characterized in that the driving machine body (7) is a steering engine or a hydraulic cylinder.
10. The transmission mechanism of the resistance rudder according to claim 2, wherein the inner side wall of the upper resistance rudder (1) is provided with a first groove, the inner side wall of the lower resistance rudder (2) is provided with a second groove, the first groove corresponds to the second groove in position and can be butted to form an accommodating space, the upper driving rod (5) is hinged in the first groove, the lower driving rod (6) is hinged in the second groove, and when the inner side wall of the upper resistance rudder (1) is butted with the inner side wall of the lower resistance rudder (2), the other ends of the upper driving rod (5), the lower driving rod (6) and the telescopic rod (10) can be placed in the accommodating space.
11. The transmission of the resistance rudder according to claim 1, characterized in that it further comprises a fixed assembly (8) hingedly arranged on the telescopic drive assembly and adapted to arrange the telescopic drive assembly on a setting member.
12. An aircraft comprising a transmission mechanism of a resistance rudder and a fuselage, characterized in that the transmission mechanism of the resistance rudder is the transmission mechanism of the resistance rudder according to any one of claims 1 to 11, the upper rotation shaft (3) and the lower rotation shaft (4) of the transmission mechanism of the resistance rudder being fixedly connected to the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111573929.XA CN114313218A (en) | 2021-12-21 | 2021-12-21 | Transmission mechanism of resistance rudder and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111573929.XA CN114313218A (en) | 2021-12-21 | 2021-12-21 | Transmission mechanism of resistance rudder and aircraft |
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| CN114313218A true CN114313218A (en) | 2022-04-12 |
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| CN202111573929.XA Pending CN114313218A (en) | 2021-12-21 | 2021-12-21 | Transmission mechanism of resistance rudder and aircraft |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6079672A (en) * | 1997-12-18 | 2000-06-27 | Lam; Lawrence Y. | Aileron for fixed wing aircraft |
| CN204489176U (en) * | 2015-03-09 | 2015-07-22 | 中国航空工业集团公司沈阳飞机设计研究所 | The drag rudder of a kind of anury Flying-wing aircraft |
| CN111380409A (en) * | 2020-03-30 | 2020-07-07 | 航天神舟飞行器有限公司 | Stealthy rudder face mounting structure of all-wing aircraft overall arrangement target drone aircraft |
| CN111891336A (en) * | 2020-09-02 | 2020-11-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Variable-configuration control surface for realizing composite control of airplane |
| CN112572769A (en) * | 2020-11-23 | 2021-03-30 | 贵州贵航飞机设计研究所 | Driving method of symmetrical speed reducing plate |
| CN213974440U (en) * | 2020-11-17 | 2021-08-17 | 贵州贵飞飞机设计研究院有限公司 | Symmetrical opening and closing mechanism of airplane resistance device |
-
2021
- 2021-12-21 CN CN202111573929.XA patent/CN114313218A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6079672A (en) * | 1997-12-18 | 2000-06-27 | Lam; Lawrence Y. | Aileron for fixed wing aircraft |
| CN204489176U (en) * | 2015-03-09 | 2015-07-22 | 中国航空工业集团公司沈阳飞机设计研究所 | The drag rudder of a kind of anury Flying-wing aircraft |
| CN111380409A (en) * | 2020-03-30 | 2020-07-07 | 航天神舟飞行器有限公司 | Stealthy rudder face mounting structure of all-wing aircraft overall arrangement target drone aircraft |
| CN111891336A (en) * | 2020-09-02 | 2020-11-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Variable-configuration control surface for realizing composite control of airplane |
| CN213974440U (en) * | 2020-11-17 | 2021-08-17 | 贵州贵飞飞机设计研究院有限公司 | Symmetrical opening and closing mechanism of airplane resistance device |
| CN112572769A (en) * | 2020-11-23 | 2021-03-30 | 贵州贵航飞机设计研究所 | Driving method of symmetrical speed reducing plate |
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