CN210691691U - External control load device for simulating aircraft pedal - Google Patents
External control load device for simulating aircraft pedal Download PDFInfo
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- CN210691691U CN210691691U CN201920590799.2U CN201920590799U CN210691691U CN 210691691 U CN210691691 U CN 210691691U CN 201920590799 U CN201920590799 U CN 201920590799U CN 210691691 U CN210691691 U CN 210691691U
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- fixing bolt
- load device
- manipulation
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Abstract
The utility model discloses a simulation aircraft pedal is with external load device that manipulates, including base platform, base platform's top is provided with pedal mechanism to base platform's side has braced frame through first fixing bolt threaded connection, braced frame's top has the pedal through second fixing bolt threaded connection to manipulate the load, pedal mechanism rotates through manipulating the load connecting rod and connects in pedal manipulation load, the utility model relates to a simulation aircraft pedal technical field. This simulation aircraft pedal is with external manipulation load device, through with the pedal manipulation load after external, the operator installation, debugging and maintenance manipulation load become very convenient, the operator can obtain bigger operating space from a plurality of azimuths around the manipulation load, when having avoided maintaining the manipulation load at every turn, the operator all must climb into work in the platform frame, can remove the outlying safety shield of braced frame, observes the behavior of inside manipulation load.
Description
Technical Field
The utility model relates to a simulation aircraft pedal technical field specifically is a simulation aircraft pedal is with external manipulation load device.
Background
The existing pedal mechanism of some simulated aircraft is installed on a steel structure base platform, a force feedback motor of the pedal mechanism is called pedal operation load and is installed in a base platform frame, the base platform is of a welded structure, and in the prior art, the pedal operation load is fixed in the steel structure base in a bolt connection mode and is called built-in pedal operation load.
The existing operation load is arranged in a base frame and is positioned below a base platform surface, a simulation aircraft cabin body is arranged above the base platform surface and comprises a central operation platform, a seat, a side lever box, a central instrument board and the like, because a simulation machine part arranged above the base platform occupies a maintenance space right above a pedal operation load, an operator can only enter a pedal operation load position from the side surface of the platform to carry out operations such as installation, debugging, maintenance and the like, the operation is limited by the height of the base platform frame, the operator is very inconvenient to get in and out of the base platform from the side surface of the platform, and the maintainability of the operation load is poor.
SUMMERY OF THE UTILITY MODEL
Not enough to prior art, the utility model provides a simulation aircraft pedal is with external manipulation load device has solved the problem that manipulation load device installation is inconvenient, maintainability is poor.
In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: the utility model provides a simulation aircraft pedal is with external load device of manipulating, includes base platform, base platform's top is provided with pedal mechanism to base platform's side has braced frame through first fixing bolt threaded connection, braced frame's top has the pedal through second fixing bolt threaded connection to manipulate the load, pedal mechanism is rotated through manipulating the load connecting rod and is connected in pedal manipulation load.
Furthermore, the side face of the supporting frame is fixedly connected with a supporting rod, and the top of the supporting rod is fixedly connected to the bottom of the supporting frame.
Furthermore, four clamping blocks are fixedly connected to the side face of the supporting frame, a side face safety baffle is clamped on the surface of each clamping block, two clamping grooves are formed in the side face of the side face safety baffle, and the clamping grooves are matched with the clamping blocks.
Further, the bottom of the side safety barrier is screwed to the top of the support frame by a third fixing bolt.
Furthermore, a front safety baffle is connected between the opposite sides of the two side safety baffles through fourth fixing bolts in a threaded mode, and the left side and the right side of the front safety baffle are provided with two fourth fixing bolts.
Furthermore, a countersunk hole is formed in the side face of the supporting frame, and the first fixing bolt is arranged inside the countersunk hole.
Compared with the prior art, the beneficial effects of the utility model are that:
(1) this simulation aircraft pedal is with external manipulation load device, through with the pedal manipulation load after external, the operator installation, the debugging becomes very convenient with the maintenance manipulation load, the operator can obtain bigger operating space from a plurality of position around the manipulation load, when having avoided maintaining the manipulation load at every turn, the operator must all work in climbing the platform frame, under the condition that need not dismantle the manipulation load and maintain, can remove the peripheral safety shield of braced frame, observe the operating conditions of inside manipulation load.
(2) This simulation aircraft pedal is with external installation of handling of load through the pedal for simple structure, install and remove the convenience, the safety shield is installed to the braced frame periphery, will handle the load and protect completely, avoids moving part and object on every side to bump, and safe and reliable handles load mounting structure modularized design, as the alternative supply of material item, can provide according to the user's demand.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic structural view of the supporting frame of the present invention;
fig. 3 is a structural plan view of the support frame of the present invention;
fig. 4 is a side partial sectional view of the support frame of the present invention.
In the figure: 1-base platform, 2-pedal mechanism, 3-first fixing bolt, 4-supporting frame, 5-second fixing bolt, 6-pedal operation load, 7-operation load connecting rod, 8-supporting rod, 9-clamping block, 10-side safety baffle, 11-clamping groove, 12-third fixing bolt, 13-fourth fixing bolt, 14-front safety baffle and 15-countersunk hole.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution: an external control load device for simulating an aircraft pedal comprises a base platform 1, wherein a pedal mechanism 2 is arranged at the top of the base platform 1, the side surface of the base platform 1 is in threaded connection with a supporting frame 4 through a first fixing bolt 3, the first fixing bolts 3 are six in total and are in a group, the supporting frame 4 is fixed at three positions, namely an upper position, a middle position and a lower position, the top of the supporting frame 4 is in threaded connection with a pedal control load 6 through a second fixing bolt 5, the second fixing bolts 5 are four in total and are arranged in four corners for fixing the pedal control load 6 on the supporting frame 4, the pedal mechanism 2 is rotatably connected with the pedal control load 6 through a control load connecting rod 7, a supporting rod 8 is fixedly connected to the side surface of the supporting frame 4, the top of the supporting rod 8 is fixedly connected to the bottom of the supporting frame 4, and the supporting rod 8 plays a supporting, the side surface of the supporting frame 4 is fixedly connected with four clamping blocks 9, the two clamping blocks 9 are in a group and are vertically arranged, the surfaces of the two clamping blocks 9 are clamped with a side surface safety baffle plate 10, the side surface of the side surface safety baffle plate 10 is provided with two clamping grooves 11, the clamping grooves 11 and the clamping blocks 9 are matched with each other, the bottom of the side surface safety baffle plate 10 is connected to the top of the supporting frame 4 through third fixing bolts 12 and threads, a front safety baffle plate 14 is connected between the opposite sides of the two side surface safety baffle plates 10 through fourth fixing bolts 13 and threads, the front safety baffle plate 14 can be detached independently through detaching the fourth fixing bolts 13 so as to observe the running condition of the internal pedal operation load 6 under the condition that the pedal operation load 6 is not required to be detached for maintenance, the left side surface and the right side surface of the front safety baffle plate 14 are provided with the two fourth fixing, first fixing bolt 3 sets up in the inside of counter sink 15, and first fixing bolt 3 is located the inside of counter sink 15, and the top surface thickness of first fixing bolt 3 is less than the degree of depth of counter sink 15.
When the device is used, the external operation load device for simulating the pedals of the aircraft is used, the supporting frame 4 is installed on the side face of the base platform 1 through the first fixing bolt (3), the pedal operation load 6 is placed at the top of the supporting frame 4, then the pedal operation load 6 is fixed at the top of the supporting frame 4 through the second fixing bolt 5, the operation load connecting rod 7 is connected with the pedal operation load 6, the side safety baffle plate 10 is clamped on the clamping block 9, the side safety baffle plate 10 is fixed on the supporting frame 4 from the bottom through the third fixing bolt 12, and the front safety baffle plate 14 is fixedly connected with the side safety baffle plate 10 through the fourth fixing screw 13.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The utility model provides a simulation aircraft pedal is with external manipulation load device, includes base platform (1), its characterized in that: the top of base platform (1) is provided with pedal mechanism (2) to the side of base platform (1) has braced frame (4) through first fixing bolt (3) threaded connection, braced frame's (4) top has pedal through second fixing bolt (5) threaded connection and manipulates load (6), pedal mechanism (2) are rotated through manipulation load connecting rod (7) and are connected in pedal manipulation load (6).
2. An external operating load device for simulating the pedal of an aircraft as claimed in claim 1, wherein: the side face of the supporting frame (4) is fixedly connected with a supporting rod (8), and the top of the supporting rod (8) is fixedly connected to the bottom of the supporting frame (4).
3. An external operating load device for simulating the pedal of an aircraft as claimed in claim 1, wherein: four fixture blocks (9) of side fixedly connected with of braced frame (4), two the surface joint of fixture block (9) has a side safety shield (10), two draw-in grooves (11) have been seted up to the side of side safety shield (10), mutually support between draw-in groove (11) and fixture block (9).
4. An external operating load device for simulating the pedal of an aircraft as claimed in claim 3, wherein: the bottom of the side safety barrier (10) is connected to the top of the supporting frame (4) through a third fixing bolt (12) in a threaded mode.
5. An external operating load device for simulating the pedal of an aircraft as claimed in claim 3, wherein: two there is positive safety shield (14) between the relative one side of side safety shield (10) through fourth fixing bolt (13) threaded connection, the both sides all are provided with two fourth fixing bolt (13) about positive safety shield (14).
6. An external operating load device for simulating the pedal of an aircraft as claimed in claim 1, wherein: the side of the supporting frame (4) is provided with a countersunk hole (15), and the first fixing bolt (3) is arranged in the countersunk hole (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920590799.2U CN210691691U (en) | 2019-04-28 | 2019-04-28 | External control load device for simulating aircraft pedal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920590799.2U CN210691691U (en) | 2019-04-28 | 2019-04-28 | External control load device for simulating aircraft pedal |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210691691U true CN210691691U (en) | 2020-06-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920590799.2U Active CN210691691U (en) | 2019-04-28 | 2019-04-28 | External control load device for simulating aircraft pedal |
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| Country | Link |
|---|---|
| CN (1) | CN210691691U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112201114A (en) * | 2020-10-12 | 2021-01-08 | 浙江大学 | Big aircraft pedal analogue means based on rack and pinion motion |
-
2019
- 2019-04-28 CN CN201920590799.2U patent/CN210691691U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112201114A (en) * | 2020-10-12 | 2021-01-08 | 浙江大学 | Big aircraft pedal analogue means based on rack and pinion motion |
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