CN205209737U - Hatch door control mechanism - Google Patents
Hatch door control mechanism Download PDFInfo
- Publication number
- CN205209737U CN205209737U CN201521037616.2U CN201521037616U CN205209737U CN 205209737 U CN205209737 U CN 205209737U CN 201521037616 U CN201521037616 U CN 201521037616U CN 205209737 U CN205209737 U CN 205209737U
- Authority
- CN
- China
- Prior art keywords
- hatch door
- driving mechanism
- rocking arm
- door control
- control gear
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Power-Operated Mechanisms For Wings (AREA)
Abstract
The utility model discloses a hatch door control mechanism. Hatch door control mechanism includes: actuating mechanism, actuating mechanism sets up on second support (3), actuating mechanism has the output, link mechanism, link mechanism one end with actuating mechanism's output is connected, and hatch door pivot (11) the transmission on hatch door (1) of the other end and model aircraft is connected, wherein, actuating mechanism is used for the drive the link mechanism motion, link mechanism is used for receiving the actuating mechanism drive, thus drive hatch door pivot campaign. The utility model provides a hatch door control mechanism both can realize the fixed angle of hatch door and open, also can simulate opening / process of closing of weapon -bay hatch door, can not the destruction test mode shape when improving test efficiency.
Description
Technical field
The utility model relates to wind-tunnel technique field, particularly relates to a kind of hatch door control gear.
Background technology
The motion of current simulated weapons cabin door in wind tunnel test, is generally realize the change of hatch door angle by angle block mode, also has a kind of method driving hatch door to move by motor-driven gear mechanism in addition.
The shortcoming of angle block method is: 1, can only simulate fixed angle; 2, test efficiency is low
The shortcoming of gear drive method is: 1, hatch door rotation process middle gear gives prominence to test model profile too much, damage model monnolithic case, impact test accuracy; 2, take up room too large, be not suitable for practical application.
Therefore, wish that a kind of technical scheme can overcome or reduce at least one shortcoming above-mentioned.
Utility model content
The purpose of this utility model is to provide a kind of hatch door control gear, to overcome or to reduce at least one shortcoming above-mentioned.
For achieving the above object, the utility model provides a kind of hatch door control gear.Hatch door control gear, for controlling the hatch door motion of model aircraft in wind tunnel test, described hatch door is provided with the first support and the second support, described second support is connected with described first support, described hatch door control gear comprises: driving mechanism, described driving mechanism is arranged on the secondary support bracket, and described driving mechanism has output terminal; Linkage assembly, described linkage assembly one end is connected with the output terminal of described driving mechanism, and the other end is connected with the hatch door rotating shaft transmission on the hatch door of model aircraft; Wherein, described driving mechanism is for driving described connecting rod mechanism movement, and described linkage assembly is used for being subject to described driving mechanism and drives, thus drives described hatch door pivot.
Preferably, described linkage assembly is four-bar mechanism.
Preferably, described driving mechanism comprises servomotor.
Preferably, described driving mechanism comprises reductor further, and the output shaft of described servomotor is connected with described reductor, and the output terminal of described reductor is connected with described linkage assembly.
Preferably, described second support comprises axis hole and drive link connecting hole, and the output terminal of described driving mechanism through described axis hole, thus is connected with described linkage assembly; Described linkage assembly through described drive link connecting hole, thus is connected with described hatch door rotating shaft.
Preferably, described three-link mechanism comprises: the first rocking arm, and described first rocking arm has the first hole, and the output terminal of described first hole and described reductor is in transmission connection; First connecting rod, one end of described first connecting rod is connected with described first rocking-arm driving; Second rocking arm, the other end of described second rocking arm and described first connecting rod is in transmission connection, and described second rocking arm has the second hole, and described second hole is connected with described hatch door rotating shaft transmission.
Preferably, described first rocking arm is connected by key with described reductor; Second rocking arm is connected by key with described hatch door rotating shaft.
Hatch door control gear in the utility model both can realize hatch door fixed angle and open, also can the opening/closing process of simulated weapons cabin door, can not failure test mode shape while raising test efficiency.
Accompanying drawing explanation
Fig. 1 is the structural representation of the hatch door control gear according to the utility model one embodiment.
Fig. 2 is the motion simulation schematic diagram of the hatch door control gear shown in Fig. 1.
Reference numeral:
| 1 | Hatch door | 6 | First rocking arm |
| 2 | First support | 7 | First connecting rod |
| 3 | Second support | 8 | Second rocking arm |
| 11 | Hatch door rotating shaft | ||
| 4 | Servomotor | ||
| 5 | Reductor |
Embodiment
The object implemented for making the utility model, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technical scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
Fig. 1 is the structural representation of the hatch door control gear according to the utility model one embodiment.Fig. 2 is the motion simulation schematic diagram of the hatch door control gear shown in Fig. 1.
Hatch door 1 is provided with the first support 2 and the second support 3, second support 3 is connected with the first support 2.
Hatch door control gear as shown in Figures 1 and 2, for controlling the hatch door motion of model aircraft in wind tunnel test, described hatch door control gear comprises driving mechanism and linkage assembly, and driving mechanism is arranged on the second support 3, and driving mechanism has output terminal; Linkage assembly one end is connected with the output terminal of driving mechanism, and the hatch door rotating shaft 11 on the hatch door 1 of the other end and model aircraft is in transmission connection; Wherein, driving mechanism is for driving described connecting rod mechanism movement, and linkage assembly is used for being subject to driving mechanism and drives, thus drives hatch door pivot.
In the present embodiment, linkage assembly is four-bar mechanism.Be understandable that, linkage assembly can also be 3 linkage assemblys, 5 linkage assemblys or other linkage assemblys, as long as can realize the purpose of this utility model.
In the present embodiment, driving mechanism comprises servomotor 4.Servomotor accurately can control rotation amount.Be understandable that, can also the motors such as stepper motor be adopted.
See Fig. 2, in the present embodiment, driving mechanism comprises reductor 5 further, and the output shaft of servomotor 4 is connected with reductor 5, and the output terminal of reductor 5 is connected with linkage assembly.Be understandable that, the rotation of hatch door is relatively slower, therefore, increases and has reductor, convenient control.
See Fig. 2, in the present embodiment, the second support 3 comprises axis hole and drive link connecting hole, and the output terminal of driving mechanism through described axis hole, thus is connected with linkage assembly; Linkage assembly through drive link connecting hole, thus is connected with hatch door rotating shaft.
See Fig. 2, in the present embodiment, institute's four-bar mechanism comprises the first rocking arm 6, first connecting rod 7 and the second rocking arm 8, first rocking arm 6 and has the first hole, and the output terminal of the first hole and reductor 5 is in transmission connection; One end and first rocking arm 6 of first connecting rod 7 are in transmission connection; Second rocking arm 8 is in transmission connection with the other end of first connecting rod 7, and the second rocking arm 8 has the second hole, and the second hole and hatch door rotating shaft 11 are in transmission connection.
In the present embodiment, the first rocking arm 6 is connected by key with reductor 5; Second rocking arm 8 is connected by key with hatch door rotating shaft 11.
Hatch door control gear in the utility model both can realize hatch door fixed angle and open, also can the opening/closing process of simulated weapons cabin door, can not failure test mode shape while raising test efficiency.
Finally it is to be noted: above embodiment only in order to the technical solution of the utility model to be described, is not intended to limit.Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment technical scheme of the utility model.
Claims (7)
1. a hatch door control gear, for controlling the hatch door motion of model aircraft in wind tunnel test, described hatch door (1) is provided with the first support (2) and the second support (3), described second support (3) is connected with described first support (2), it is characterized in that, described hatch door control gear comprises:
Driving mechanism, described driving mechanism is arranged on the second support (3), and described driving mechanism has output terminal;
Linkage assembly, described linkage assembly one end is connected with the output terminal of described driving mechanism, and the hatch door rotating shaft (11) on the hatch door (1) of the other end and model aircraft is in transmission connection; Wherein,
Described driving mechanism is for driving described connecting rod mechanism movement, and described linkage assembly is used for being subject to described driving mechanism and drives, thus drives described hatch door pivot.
2. hatch door control gear as claimed in claim 1, it is characterized in that, described linkage assembly is four-bar mechanism.
3. hatch door control gear as claimed in claim 2, it is characterized in that, described driving mechanism comprises servomotor (4).
4. hatch door control gear as claimed in claim 3, it is characterized in that, described driving mechanism comprises reductor (5) further, the output shaft of described servomotor (4) is connected with described reductor (5), and the output terminal of described reductor (5) is connected with described linkage assembly.
5. hatch door control gear as claimed in claim 1, it is characterized in that, described second support (3) comprises axis hole and drive link connecting hole, and the output terminal of described driving mechanism through described axis hole, thus is connected with described linkage assembly; Described linkage assembly through described drive link connecting hole, thus is connected with described hatch door rotating shaft.
6. hatch door control gear as claimed in claim 4, it is characterized in that, described four-bar mechanism comprises:
First rocking arm (6), described first rocking arm (6) has the first hole, and the output terminal of described first hole and described reductor (5) is in transmission connection;
First connecting rod (7), one end and described first rocking arm (6) of described first connecting rod (7) are in transmission connection;
Second rocking arm (8), described second rocking arm (8) is in transmission connection with the other end of described first connecting rod (7), described second rocking arm (8) has the second hole, and described second hole and described hatch door rotating shaft (11) are in transmission connection.
7. hatch door control gear as claimed in claim 6, it is characterized in that, described first rocking arm (6) is connected by key with described reductor (5); Second rocking arm (8) is connected by key with described hatch door rotating shaft (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521037616.2U CN205209737U (en) | 2015-12-13 | 2015-12-13 | Hatch door control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521037616.2U CN205209737U (en) | 2015-12-13 | 2015-12-13 | Hatch door control mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205209737U true CN205209737U (en) | 2016-05-04 |
Family
ID=55847446
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521037616.2U Active CN205209737U (en) | 2015-12-13 | 2015-12-13 | Hatch door control mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205209737U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989919A (en) * | 2017-06-08 | 2017-07-28 | 北京航空航天大学 | A kind of aircraft door fatigue experimental device |
-
2015
- 2015-12-13 CN CN201521037616.2U patent/CN205209737U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989919A (en) * | 2017-06-08 | 2017-07-28 | 北京航空航天大学 | A kind of aircraft door fatigue experimental device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103552689B (en) | Minitype ornithopter wing driving mechanism with changeable wing area | |
| CN203719075U (en) | Automatic swing mechanism and air conditioner with same | |
| CN111591462A (en) | Helicopter tail rotor simulation system for wind tunnel test | |
| CN205209737U (en) | Hatch door control mechanism | |
| CN103615793A (en) | Air conditioner capable of blowing air in optional directions | |
| CN203838956U (en) | Crank rocking bar mechanism demonstration apparatus | |
| CN205113712U (en) | Two degree of freedom flapping wing aircraft | |
| CN204937479U (en) | A kind of folded wing assembly and there is its aircraft | |
| CN110371288A (en) | One kind is fluttered the adjustable bionic flapping-wing flying vehicle in amplitude angle | |
| CN105539821A (en) | Deformable folding structure of multi-rotor type aircraft | |
| CN203383707U (en) | Electric vertical curtain | |
| CN202742253U (en) | Locating mechanism | |
| CN110356552B (en) | Direct-acting double-flapping-wing unmanned aerial vehicle with rotatable blades | |
| CN201772595U (en) | Automobile air conditioner air door controller | |
| CN204433037U (en) | The servo-actuated seal structure of a kind of vehicle rudder leading edge | |
| CN210890129U (en) | Connecting rod structure of air valve | |
| CN201678042U (en) | Rotary flapping wing aerocraft | |
| CN110294121B (en) | Direct-acting four-flapping-wing unmanned aerial vehicle based on self-adaptive airflow rotatable blades | |
| CN209600793U (en) | A kind of flap gear | |
| CN206756423U (en) | A kind of carrier aircraft support prepared for captive trajectory testing ground | |
| CN205741997U (en) | A kind of fan door module for passageway gate machine | |
| CN208377059U (en) | A kind of unmanned plane rotor inclining rotary mechanism of spherical gear auxiliary driving | |
| CN103292444A (en) | Connecting-rod-type folio leaf damper | |
| CN206567591U (en) | A kind of modified plate clipping device | |
| CN202066168U (en) | Wind power transmission wind outlet structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |