CN111099034A - Torsion type airplane control human sensing mechanism with adjustable starting torque and adjusting method - Google Patents
Torsion type airplane control human sensing mechanism with adjustable starting torque and adjusting method Download PDFInfo
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- CN111099034A CN111099034A CN201911282527.7A CN201911282527A CN111099034A CN 111099034 A CN111099034 A CN 111099034A CN 201911282527 A CN201911282527 A CN 201911282527A CN 111099034 A CN111099034 A CN 111099034A
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- adjusting
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- adjusting disc
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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
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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
- B64C13/04—Initiating means actuated personally
- B64C13/042—Initiating means actuated personally operated by hand
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention belongs to the technical field of design of an airplane control human sensing system, and particularly relates to a torsion type airplane control human sensing mechanism with adjustable starting torque and an adjusting method. At present, the torsion type force-sensing starting force is not easy to be accurately adjusted, a plurality of processing parts are provided, a plurality of materials are consumed, the volume and the weight of the mechanism are increased, and the starting force is adjusted more complicatedly. The first adjusting disc and the second adjusting disc are provided with a plurality of countersunk holes in the circumferential direction and are respectively provided with a second arc bulge and a third arc bulge; the twisting body has twisting elasticity, and a plurality of threaded holes are formed in the end faces of the two sides of the twisting body; the rotating shaft sequentially penetrates through the first adjusting disc, the twisting body, the second adjusting disc and the anchoring disc. The adjustment of the force-sensitive starting force of the airplane operation torsion body is accurately, simply and efficiently completed by adjusting different installation angle positions of the first adjusting disc and the second adjusting disc on the torsion body, the used parts are few, the reliability is high, the material consumption is low, the size and the weight of the mechanism are reduced, and the cost is reduced.
Description
Technical Field
The invention belongs to the technical field of design of an airplane control human sensing system, and particularly relates to a torsion type airplane control human sensing mechanism with adjustable starting torque and an adjusting method.
Background
A manual feeling force system is arranged in a modern aircraft cockpit control system to provide control force simulation, so that a pilot can intuitively feel the state of the aircraft, and the situation that the pilot mistakenly operates to influence the safety and flight control quality of the aircraft is avoided. The artificial sensory force system needs to have a centering function, and thus a certain preload force, i.e., a starting force, needs to be set to a spring of the artificial sensory force system. The pilot signal is output when the pilot's actuating force on the steering column is greater than the starting force. In order to ensure the accuracy of the actuating force, the actuating force of the spring needs to be adjusted. At present, the difficult adjustment of system start-up power is felt to torsional mode power, and the consumptive material is hard, has increased mechanism volume and weight simultaneously.
Disclosure of Invention
The purpose of the invention is: aiming at the defects of the existing adjustment of the force sensing starting force of the airplane control torsion body, the torsion type airplane control human sensing mechanism with the adjustable starting moment and the adjusting method are provided, so that the problem that the existing torsion type force sensing starting force is not easy to adjust accurately is solved, a plurality of parts are used, a plurality of materials are consumed, the size and the weight of the mechanism are increased, the defects of complicated adjustment of the starting force and the like are overcome, the accuracy, the operability and the production efficiency of the adjustment of the starting force of the airplane control force sensing system are improved, and the weight, the size and the cost are reduced.
The technical scheme of the invention is as follows: a torsion type airplane control human body mechanism with adjustable starting torque comprises a rotating shaft, a first adjusting disc, a torsion body, a second adjusting disc and an anchoring disc, wherein the first adjusting disc and the second adjusting disc are provided with a plurality of countersunk holes in the circumferential direction and are respectively provided with a second arc bulge and a third arc bulge; the twisting body has twisting elasticity, and a plurality of threaded holes are formed in the end faces of the two sides of the twisting body; the rotating shaft sequentially passes through the first adjusting disc, the twisting body, the second adjusting disc and the anchoring disc, a first arc bulge of the rotating shaft on a twisting arm of the rotating shaft and a fourth arc bulge of the anchoring disc have the same circumferential span, and the rotating shaft is clamped between the second arc bulge and the third arc bulge in the circumferential direction; the relative position of the countersunk hole and the threaded hole is adjusted to change the included angle between the second arc protrusion and the third arc protrusion, and the second arc protrusion and the third arc protrusion are connected through screws.
Furthermore, the first adjusting disc and the second adjusting disc are provided with the same sets of m countersunk hole groups, each countersunk hole group is uniformly distributed on the circumference and is spaced at a certain angle, n countersunk holes are arranged in each set, the hole pitch is α degrees consistently, m threaded hole groups are arranged on the end face of the twisting body, each threaded hole group is uniformly distributed on the circumference and is spaced at a certain angle, n threaded holes are arranged in each set, the hole pitch is β degrees consistently, the angle difference between α and β is delta degrees, and the starting force adjusting precision value is achieved by designing the size of the angle difference delta.
Furthermore, the first adjusting disk and the second adjusting disk are provided with the same group number m of countersunk hole groups, each countersunk hole group is uniformly distributed on the circumference and has a certain angle at intervals, n countersunk holes are arranged in the group, and the hole distances are consistent; the end face of the twisting body is provided with m threaded hole groups, each threaded hole group is uniformly distributed on the circumference at a certain angle, n threaded holes are formed in the groups, and the hole distances are increased in an equal difference mode.
Furthermore, a spiral groove is machined on the cylindrical surface of the annular structure body in a machining mode to form the twisting body, and the spiral groove penetrates through the cylindrical surface.
Furthermore, m is more than two groups.
Further, n has a value of at least 2.
Further, the rotating shaft is provided with a radial torque arm, and an axial first arc bulge is arranged at the end part of the torque arm.
Further, the first adjusting disc and the second adjusting disc are respectively provided with a second circular arc bulge and a third circular arc bulge in the axial direction at the edge; the first adjusting disk also has a first hollow shaft, the second adjusting disk also has a second hollow shaft, and the anchor disk also has a third hollow shaft
Further, the anchoring disc has gear teeth on an annular face for anchoring by engaging with an external structure.
The invention also provides a method for adjusting the torsional type airplane control human sensing mechanism, which utilizes the torsional type airplane control human sensing mechanism with adjustable starting moment and comprises the following steps:
s1, adjusting the first adjusting disk and the second adjusting disk to have a certain included angle in advance, and fixing the first adjusting disk and the second adjusting disk on the twisting body through screws in the corresponding hole group;
s2, measuring a starting torque;
s3, according to the difference value between the measured value and the requirement value of the starting force, the screw is disassembled, the included angle between the first adjusting disk and the second adjusting disk is adjusted, and if the difference value does not meet the requirement value of the starting force, the step S2 is returned; the required value of the starting force is satisfied, and the process proceeds to step S4;
and S4, fixing the first adjusting disk and the second adjusting disk on the twisting body in the corresponding hole groups through screws.
The invention has the advantages that: the torsion type airplane control human sensing mechanism with adjustable starting moment and the adjusting method can accurately, simply and efficiently finish the adjustment of the airplane control torsion type force sensing starting force by adjusting different installation angle positions of the first adjusting disc and the second adjusting disc on the torsion body, and has the advantages of less used parts, high reliability, less material consumption, reduced mechanism volume and weight and reduced cost.
Drawings
FIG. 1 is a schematic view of a twist-type airplane manipulator mechanism according to the present invention;
FIG. 2 is a schematic view of a spindle of the present invention;
FIG. 3 is a first dial illustration of the present invention;
FIG. 4 is a schematic view of a twisting body of the present invention;
FIG. 5 is a second dial illustration of the present invention;
FIG. 6 is an illustration of the anchor plate of the present invention;
wherein: 1-rotating shaft, 2-first adjusting disk, 3-twisting body, 4-second adjusting disk, 5-anchoring disk, 6-screw, 1 a-first arc bulge, 1 b-twisting arm, 2 a-second arc bulge, 2 b-second arc side surface, 2 c-first countersunk hole, 2 d-first hollow shaft, 3 a-threaded hole, 3 b-end surface, 4 a-third arc bulge, 4 b-third arc side surface, 4 c-second countersunk hole, 4 d-second hollow shaft, 5 a-fourth arc bulge, 5 b-gear tooth, 5 c-third hollow shaft
Detailed Description
Referring to fig. 1 to 6, specific embodiments are provided: a torsion type airplane control human body mechanism with adjustable starting moment and an adjusting method thereof comprise a rotating shaft 1, a first adjusting disk 2, a torsion body 3, a second adjusting disk 4 and an anchoring disk 5.
The circumference of the first adjusting disk 2 and the second adjusting disk 4 is respectively provided with a first arc bulge 1a and a second arc bulge 2a along the axial direction on the side surface, and is respectively provided with a first counter sink 2c and a second counter sink 4c on the other side surface, the first adjusting disk 2 and the second adjusting disk 4 are respectively provided with 3 counter sink groups, each counter sink group is uniformly distributed on the circumference and has 120 intervals, each group is provided with 5 counter sinks, and the hole distances are consistent to 15 degrees; the twisting body 3 is formed by machining a spiral groove on the cylindrical surface of the annular structure body in a mechanical machining mode, and the spiral groove penetrates through the cylindrical surface, but other machining modes are not excluded; the twisting body 3 has twisting elasticity, 3 threaded hole groups are arranged on two end faces 3b of the twisting body 3, each threaded hole group is uniformly distributed on the circumference and is at equal intervals, 5 threaded holes are arranged in each group, and the hole distances are consistent and are 15.2 degrees; the difference between the distances between the countersunk heads on the first adjusting disk 2 and the second adjusting disk 4 and the distances between the threaded holes on the two end faces 3b of the twisting body 3 is 15.2 degrees minus 15 degrees and is equal to 0.2 degrees, namely the starting force adjustment precision value is 0.2 degrees.
The rotating shaft 1 is constrained to rotate around an axis X, and the rotating shaft 1 sequentially passes through the first adjusting disk 2, the twisting body 3, the second adjusting disk 4 and the anchoring disk 5; the first adjusting disc 2 and the second adjusting disc 4 are respectively provided with a second circular arc bulge 2a and a third circular arc bulge 4a in the axial direction at the edge; the first adjusting disk 2 also has a first hollow shaft 2d, the second adjusting disk 4 also has a second hollow shaft 4d, and the anchoring disk 5 also has a third hollow shaft 5 c; the first adjusting disk 2, the second adjusting disk 4 and the anchoring disk 5 can coaxially and relatively rotate around the rotating shaft 1; the rotating shaft 1 is provided with a radial torque arm 1b, and an axial first arc bulge 1a is arranged at the end part of the torque arm 1 b; a first circular arc bulge 1a of the rotating shaft 1 on a torsion arm 1b thereof and a fourth circular arc bulge 5a of the anchoring disc 5 are simultaneously clamped between a second circular arc bulge 2a and a third circular arc bulge 4a which are axially and oppositely staggered in the circumferential direction; the circumferential angles of the first circular arc protrusion 1a and the fourth circular arc protrusion 5a are the same.
The included angle between the second arc protrusion 2a and the third arc protrusion 4a is changed by adjusting the relative positions of the countersunk holes and the threaded holes, and 3 countersunk holes with the same phase in 3 groups of countersunk holes correspond to the corresponding threaded holes 3a on the torsion body 3 and are fixedly connected by screws 6. The angle between the second 2a and third 4a protrusions will change by 0.2 deg., and the clamping force, i.e. the starting force, between the second 2a and third 4a protrusions will change.
The anchoring disc 5 has gear teeth 5b on the annular face, anchored by engagement with an external locking mechanism.
Adjusting the starting force according to the following steps:
s1, preliminarily adjusting the first adjusting disk 2 and the second adjusting disk 4 to have a certain included angle, and fixing the first adjusting disk and the second adjusting disk on the twisting body 3 through screws 6 in the corresponding hole groups;
s2, measuring a starting torque;
s3, according to the difference between the measured value and the required value of the starting force, the screw 6 is disassembled, the included angle between the first adjusting disk 2 and the second adjusting disk 4 is adjusted, and if the required value of the starting force is not met, the step S2 is returned; the required value of the starting force is satisfied, and the process proceeds to step S4;
s4, the first adjustment disk 2 and the second adjustment disk 4 are fixed to the torsion body 3 by screws 6 in the corresponding hole groups.
Claims (10)
1. The utility model provides a people mechanism is felt to torsional type aircraft manipulation of starting moment adjustable, includes pivot (1), its characterized in that: the mechanism further comprises a first adjusting disc (2), a twisting body (3), a second adjusting disc (4) and an anchoring disc (5), wherein the first adjusting disc (2) and the second adjusting disc (4) are provided with a plurality of countersunk holes in the circumferential direction and are respectively provided with a second arc protrusion (2a) and a third arc protrusion (4 a); the twisting body (3) has twisting elasticity, and a plurality of threaded holes are formed in the end faces (3b) on the two sides; the rotating shaft (1) sequentially penetrates through the first adjusting disc (2), the twisting body (3), the second adjusting disc (4) and the anchoring disc (5), a first circular arc bulge (1a) of the rotating shaft (1) on a twisting arm (1b) of the rotating shaft and a fourth circular arc bulge (5a) of the anchoring disc (5) have the same circumferential span, and the rotating shaft is clamped between the second circular arc bulge (2a) and the third circular arc bulge (4a) in the circumferential direction; the relative position of the countersunk hole and the threaded hole is adjusted to change the included angle between the second arc-shaped bulge (2a) and the third arc-shaped bulge (4a), and the second arc-shaped bulge and the third arc-shaped bulge are connected by a screw (6).
2. The torsional type aircraft manipulator mechanism of claim 1, wherein the first adjusting disk (2) and the second adjusting disk (4) are provided with the same group number m of countersunk hole groups, each countersunk hole group is uniformly distributed on the circumference and is spaced at a certain angle, n countersunk holes are formed in each group, the hole distance is α degrees, m threaded hole groups are formed in the end face (3b) of the twisting body (3), each threaded hole group is uniformly distributed on the circumference and is spaced at a certain angle, n threaded holes are formed in each group, the hole distance is β degrees, the angle difference between α and β is delta degrees, and the starting force adjusting precision value is achieved by designing the size of the angle difference delta.
3. The twisted aircraft manipulator mechanism of claim 1, wherein: the first adjusting disc (2) and the second adjusting disc (4) are provided with the same group number m of countersunk hole groups, each countersunk hole group is uniformly distributed on the circumference and is spaced at a certain angle, n countersunk holes are arranged in the group, and the hole distances are consistent; the end face (3b) of the twisting body (3) is provided with m thread hole groups, each thread hole group is uniformly distributed on the circumference and has a certain angle at intervals, n thread holes are arranged in the groups, and the hole distances are increased in an equal difference mode.
4. A twisted aircraft manipulator mechanism according to any of claims 1-3, wherein: and a spiral groove is machined on the cylindrical surface of the annular structure body in a machining mode to form the twisting body (3), and the spiral groove penetrates through the cylindrical surface.
5. A twisted aircraft manipulator mechanism according to any of claims 1-3, wherein: m is more than two groups.
6. The twisted aircraft manipulator mechanism of claim 5, wherein: n has a value of at least 2.
7. A twisted aircraft manipulator mechanism according to any of claims 1-3, wherein: the rotating shaft (1) is provided with a radial torque arm (1b), and an axial first arc bulge (1a) is arranged at the end part of the torque arm (1 b).
8. A twisted aircraft manipulator mechanism according to any of claims 1-3, wherein: the first adjusting disc (2) and the second adjusting disc (4) are respectively provided with a second circular arc bulge (2a) and a third circular arc bulge (4a) in the axial direction at the edge; the first adjusting disk (2) further has a first hollow shaft (2d), the second adjusting disk (4) further has a second hollow shaft (4d), and the anchoring disk (5) further has a third hollow shaft (5 c).
9. A twisted aircraft manipulator mechanism according to any of claims 1-3, wherein: the anchoring disk (5) has gear teeth (5b) on the annular surface, which are anchored by engagement with an external structure.
10. A method for adjusting a twisted type aircraft operator control mechanism, which utilizes the twisted type aircraft operator control mechanism with adjustable starting moment according to any one of claims 1 to 9, and is characterized by comprising the following steps:
s1, adjusting the first adjusting disk (2) and the second adjusting disk (4) to have a certain included angle in advance, and fixing the adjusting disks on the twisting body (3) through screws (6) in corresponding hole groups;
s2, measuring a starting torque;
s3, according to the difference value between the measured value and the requirement value of the starting force, the screw (6) is disassembled, the included angle between the first adjusting disk (2) and the second adjusting disk (4) is adjusted, and if the requirement value of the starting force is not met, the step S2 is returned; the required value of the starting force is satisfied, and the process proceeds to step S4;
and S4, fixing the first adjusting disk (2) and the second adjusting disk (4) on the twisting body (3) in the corresponding hole groups through screws (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911282527.7A CN111099034A (en) | 2019-12-13 | 2019-12-13 | Torsion type airplane control human sensing mechanism with adjustable starting torque and adjusting method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911282527.7A CN111099034A (en) | 2019-12-13 | 2019-12-13 | Torsion type airplane control human sensing mechanism with adjustable starting torque and adjusting method |
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| Publication Number | Publication Date |
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| CN111099034A true CN111099034A (en) | 2020-05-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911282527.7A Pending CN111099034A (en) | 2019-12-13 | 2019-12-13 | Torsion type airplane control human sensing mechanism with adjustable starting torque and adjusting method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550677A (en) * | 2020-12-11 | 2021-03-26 | 兰州飞行控制有限责任公司 | Structure and method for adjusting starting preload of torsional artificial sensory force |
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| GB2063786A (en) * | 1979-11-23 | 1981-06-10 | Sfena | Rotary actuator incorporating artificial feel components |
| US20090189024A1 (en) * | 2004-06-29 | 2009-07-30 | Sagem Defence Securite | Device for Remotely Controlling Aircraft Control Surfaces |
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