CN114049814B - Aircraft additional lift simulation device and control method thereof - Google Patents
Aircraft additional lift simulation device and control method thereof Download PDFInfo
- Publication number
- CN114049814B CN114049814B CN202111586132.3A CN202111586132A CN114049814B CN 114049814 B CN114049814 B CN 114049814B CN 202111586132 A CN202111586132 A CN 202111586132A CN 114049814 B CN114049814 B CN 114049814B
- Authority
- CN
- China
- Prior art keywords
- wing
- additional lift
- roll
- simulation device
- aircraft
- 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
- 238000004088 simulation Methods 0.000 title claims abstract description 103
- 238000000034 method Methods 0.000 title claims description 6
- 230000007246 mechanism Effects 0.000 claims abstract description 57
- 230000009467 reduction Effects 0.000 claims abstract description 14
- 238000005096 rolling process Methods 0.000 claims description 89
- 230000001808 coupling effect Effects 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 3
- 239000011295 pitch Substances 0.000 claims 30
- 201000009482 yaws Diseases 0.000 claims 3
- 238000005516 engineering process Methods 0.000 abstract description 4
- 230000008878 coupling Effects 0.000 abstract description 2
- 238000010168 coupling process Methods 0.000 abstract description 2
- 238000005859 coupling reaction Methods 0.000 abstract description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
-
- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/10—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer with simulated flight- or engine-generated force being applied to aircraft occupant
-
- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/16—Ambient or aircraft conditions simulated or indicated by instrument or alarm
- G09B9/20—Simulation or indication of aircraft attitude
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Physics & Mathematics (AREA)
- Educational Administration (AREA)
- Educational Technology (AREA)
- General Physics & Mathematics (AREA)
- Toys (AREA)
Abstract
本发明涉及一种飞机附加升力模拟装置，属于航空理论教学技术领域。包括副翼附加升力模拟机构、尾翼附加升力模拟机构、支撑座、摇摆机构，其中，副翼附加升力模拟机构包括结构相同第一变距涵道螺旋桨和第二变距涵道螺旋桨，两个螺旋桨的旋转分别由两个旋翼直流减速电机驱动，两个螺旋桨的桨距角由两个桨距角控制步进电机驱动，尾翼附加升力模拟机构包括结构相同的第一滚转翼和第二滚转翼，滚转翼包括中心轴，中心轴前后两端均安装有十字型桨叶架，两个十字型桨叶架上安装有四个桨叶，中心轴前端设有用于实现桨叶偏转的偏置机构。本发明能够复现飞机附加升力发生、耦合和控制。
The present invention relates to an aircraft additional lift simulation device, belonging to the field of aviation theory teaching technology. It includes an aileron additional lift simulation mechanism, a tail wing additional lift simulation mechanism, a support seat, and a swing mechanism, wherein the aileron additional lift simulation mechanism includes a first variable pitch ducted propeller and a second variable pitch ducted propeller with the same structure, the rotation of the two propellers is driven by two rotor DC reduction motors respectively, and the pitch angles of the two propellers are driven by two pitch angle control stepper motors, and the tail wing additional lift simulation mechanism includes a first roll wing and a second roll wing with the same structure, and the roll wing includes a central axis, and cross-shaped blade racks are installed at both ends of the central axis, and four blades are installed on the two cross-shaped blade racks, and a biasing mechanism for realizing blade deflection is provided at the front end of the central axis. The present invention can reproduce the generation, coupling and control of aircraft additional lift.
Description
Technical Field
The invention relates to an aircraft additional lift simulation device, and belongs to the technical field of flight training.
Background
The additional lift force is a basic element for controlling the flight of the aircraft, is usually presented in a static display mode, a virtual display mode and the like in ground teaching, and currently, no publication for simulating the additional lift force by utilizing a physical structure is seen. In practical teaching training, in many situations, the control of the state of the aircraft in the air needs to be reproduced, particularly the control of the aircraft in an unstable state, and the entity additional lift simulation technology is lacked, so that the teaching training condition with strong pertinence is difficult to be created, and the teaching training effect is influenced.
Disclosure of Invention
The invention provides an aircraft additional lift simulation device capable of reproducing the generation, coupling and control of the aircraft additional lift, aiming at solving the problem of simulating the aircraft additional lift on the ground.
In order to achieve the above purpose, the present invention provides the following technical solutions:
The aircraft additional lift simulation device is characterized by comprising an aileron additional lift simulation mechanism, a tail wing additional lift simulation mechanism, a supporting seat 17 and a swinging mechanism, wherein the aileron additional lift simulation mechanism comprises a first variable-pitch ducted propeller 1 and a second variable-pitch ducted propeller 2 which have the same structure, the rotation of the two propellers is respectively driven by two rotor direct current gear motors, the pitch angles of the two propellers are driven by two pitch angle control stepping motors, the opposite surfaces of the two variable-pitch ducted propellers are provided with a first rotating shaft 3, one end of the two first rotating shafts 3 is inserted into a cross arm 4, the cross arm 4 is connected with the swinging mechanism, the tail wing additional lift simulation mechanism comprises a first rolling wing 5 and a second rolling wing 6 which have the same structure, the two rolling wings are arranged on the rolling wing bracket 7, the rolling wings comprise a central shaft 22, the front end and the rear end of the central shaft 22 are provided with cross-shaped blade frames 23, the two cross-shaped blade frames 23 are provided with four blades 24, the front end of the central shaft 22 is provided with a biasing mechanism 25 for realizing the deflection of the blades 24, the biasing mechanism 25 is driven by a blade vertical deflection angle control stepping motor 29 arranged on the rolling wing bracket 7, the blade frames 23 are driven by a rolling wing direct current speed reduction motor 30, a rotor wing direct current speed reduction motor, a pitch angle control stepping motor, a blade vertical deflection angle control stepping motor 29 and a rolling wing direct current speed reduction motor 30 are controlled by an automatic controller, and the automatic controller is connected with an operating lever through a host;
the aircraft additional lift simulation device further comprises a foot rudder, wherein the foot rudder is connected with an automatic controller through a host, the automatic controller drives a blade lateral deflection angle to control a stepping motor to work, and the blade lateral deflection angle controls the stepping motor to control a biasing mechanism 25 to act laterally;
the automatic controller is a PLC or a singlechip;
The swinging mechanism comprises a small cross-shaped connecting piece 8 and a large cross-shaped connecting piece 9, wherein the small cross-shaped connecting piece 8 realizes the fixed connection of a cross arm 4 and a longitudinal shaft 10, the longitudinal shaft 10 passes through the large cross-shaped connecting piece 9 and then is connected with the head end of a rolling wing bracket 7 through a height adjusting mechanism, a speed damper 31 is arranged between the longitudinal shaft 10 and the large cross-shaped connecting piece 9, the large cross-shaped connecting piece 9 is arranged on a U-shaped support arm 12 through a transverse shaft 11, a vertical shaft 13 is arranged at the bottom of the U-shaped support arm 12, the bottom of the vertical shaft 13 is rotatably arranged on a supporting seat 17, pitch balance springs 14 are arranged at two ends of the transverse shaft 11 positioned at the outer side of the U-shaped support arm 12, the length direction of the pitch balance springs 14 is parallel to the height direction of the U-shaped support arm 12, a first U-shaped plug 15 capable of adjusting the position up and down is arranged at the bottom of the vertical shaft 13, the yaw balance springs 16 are parallel to the longitudinal shaft 10, and a second U-shaped plug 18 capable of adjusting the distance relative to the vertical shaft 13 is arranged on the upper surface of the supporting seat 17;
the height adjusting mechanism comprises a height adjusting block 19 connected with the longitudinal shaft 10, a height adjusting plate 20 is inserted in the height adjusting block 19, two rows of height adjusting holes 32 are formed along the height direction of the height adjusting block 19, the height adjusting plate 20 is provided with two rows of height adjusting holes with the same width, and the height adjusting plate 20 is connected with the rolling wing bracket 7 through a connecting plate 21;
The biasing mechanism 25 comprises a biasing ring 26 and four cross-shaped biasing rods 27 arranged on the outer circumference of the biasing ring 26, the biasing ring 26 is sleeved on a biasing shaft 28, and one end of each biasing rod 27 is hinged to the corresponding blade 24.
The invention relates to a control method of an aircraft additional lift simulation device, which is characterized by comprising the following steps of:
1) Simulating aircraft roll
When the control rod presses the right, the stepping motor is controlled by the two pitch angles to deflect the blades of the first variable-pitch ducted propeller 1 and the second variable-pitch ducted propeller 2 respectively, the leading edge of the blade of the first variable-pitch ducted propeller 1 deflects downwards to generate downward pulling force, and the leading edge of the blade of the second variable-pitch ducted propeller 2 deflects upwards to generate upward pulling force, so that the additional lift simulation device rolls right;
When the control rod presses the rod leftwards, the stepping motors are controlled by two pitch angles to respectively deflect the blades of the first variable-pitch ducted propeller 1 and the second variable-pitch ducted propeller 2, the leading edge of the blade of the first variable-pitch ducted propeller 1 deflects upwards to generate upward pulling force, and the leading edge of the blade of the second variable-pitch ducted propeller 2 deflects downwards to generate downward pulling force to enable the additional lift force simulation device to roll leftwards;
The speed damper 31 can restrict the rolling speed of the additional lift simulation device, so that the rolling angle speed of the additional lift simulation device is in direct proportion to the compression bar quantity of the control rod, and the rolling yaw moment can be generated by rotating the first rotating shaft 3 to enable the rear edges of the first variable-pitch ducted propeller 1 and the second variable-pitch ducted propeller 2 to deflect downwards, so that the simulation of the rolling yaw coupling effect of the aircraft is realized.
2) Simulating aircraft pitch
The two rolling wing direct current gear motors 30 drive the blade frames 23 of the first rolling wing 5 and the second rolling wing 6 to rotate at the same speed, the blades 24 do circular motion, when no manipulation is input, the rolling wings do not generate tensile force, the additional lift simulation device does not pitch, when the control rod pulls backwards, the two blade vertical deflection angles control the stepping motors 29 to respectively deflect the blades 24 of the first rolling wing 5 and the second rolling wing 6, and the front edges of the blades 24 of the first rolling wing 5 and the second rolling wing 6 deflect downwards to generate downward tensile force so as to enable the additional lift simulation device to tilt upwards;
When the operating lever pushes the rod forwards, the stepping motor 29 is controlled by the vertical deflection angles of the two paddles to deflect the paddles 24 of the first rolling wing 5 and the second rolling wing 6 respectively, and the front edges of the paddles 24 of the first rolling wing 5 and the second rolling wing 6 deflect upwards to generate upward pulling force so as to enable the additional lift simulation device to dip downwards;
Along with the pitching motion of the additional lift simulation device, the two pitching balance springs 14 deform, and when moment balance is formed between the two pitching balance springs and the tensile force generated by the two rolling wings, the additional lift simulation device is stabilized at a certain angle, so that the pitching control simulation of the aircraft is realized, and the pitching simulation of the aircraft with different pitching performances is realized by adjusting the high and low positions of the first U-shaped plug pins 15.
3) Simulation of aircraft yaw
The two rolling wing direct current speed reducing motors 30 drive the blade frames 23 of the first rolling wing 5 and the second rolling wing 6 to rotate at the same speed, when no manipulation is input, the rolling wings do not generate tensile force, the additional lift simulation device does not yaw, when the right foot rudder is kicked, the stepping motors 29 are controlled by the two blade transverse deflection angles to respectively deflect the blades 24 of the first rolling wing 5 and the second rolling wing 6, the front edges of the blades 24 of the first rolling wing 5 and the second rolling wing 6 deflect left, and left tensile force is generated, so that the additional lift simulation device yaw rightwards;
When a left foot rudder is kicked, the stepping motors are controlled through the transverse deflection angles of the two paddles to respectively deflect the paddles 24 of the first rolling wing 5 and the second rolling wing 6, and the front edges of the paddles 24 of the first rolling wing 5 and the second rolling wing 6 deflect right to generate rightward pulling force so as to enable the additional lift force simulation device to yaw leftwards;
Along with the yaw movement of the additional lift simulation device, the two yaw balance springs 16 deform, when the moment formed by the tensile force generated by the two rolling wings is balanced, the additional lift simulation device is stabilized at a certain angle, the yaw control simulation of the aircraft is realized, the yaw rolling moment can be generated by adjusting the installation height of the additional lift simulation mechanism of the tail wing, the simulation of the yaw rolling coupling effect of the aircraft is realized, and the yaw simulation of the aircraft with different yaw performances is realized by adjusting the far and near positions of the second U-shaped plug 18.
According to the aircraft additional lift simulation device, the aircraft flight control law can be simulated through the aileron additional lift simulation mechanism and the tail wing additional lift simulation mechanism. In a specific situation, the state of the aircraft is controlled by utilizing the additional lifting force, the aircraft is quite complicated, the special state of the aircraft is quite difficult to change, and the ordinary simulator cannot conduct targeted training. The additional lift simulation device provided by the invention provides a physical framework, can simulate the flight state and the maneuvering control of a special-condition airplane, finish maneuvering training beyond program exercise, and strengthen the undescribeable skills in the driving technology.
Drawings
FIG. 1 is a schematic illustration of the structure of an aircraft add-on lift simulation device of the present invention;
FIG. 2 is a schematic view of the structure of a rocking mechanism 1;
FIG. 3 is a schematic view of the structure of the rocking mechanism 2;
fig. 4 is a schematic view of the structure of the roll wing and the biasing mechanism.
In the figure: 1. a first variable pitch ducted propeller; 2. the second variable-pitch ducted propeller; 3. a first rotating shaft; 4. a cross arm; 5. a first roll wing; 6. a second roll wing; 7. a roll wing bracket; 8. a small cross-shaped connector; 9. a large cross-shaped connecting piece; 10. a longitudinal axis; 11. a horizontal axis; 12. u-shaped support arms; 13. a vertical axis; 14. a pitch balancing spring; 15. a first U-shaped bolt; 16. a yaw balance spring; 17. a support base; 18. a second U-shaped bolt; 19. a height adjusting block; 20. a height adjusting plate; 21. a connecting plate; 22. a central shaft; 23. a cross-shaped blade frame; 24. a paddle; 25. a biasing mechanism; 26. a bias ring; 27. a biasing lever; 28. a bias shaft; 29. controlling a stepping motor by a vertical deflection angle of the blade; 30. a rolling wing direct current speed reducing motor; 31. A speed damper; 32. and a height adjusting hole.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
1-4, The aircraft additional lift simulation device of the embodiment comprises an aileron additional lift simulation mechanism, a tail wing additional lift simulation mechanism, a supporting seat 17 and a swinging mechanism, wherein the aileron additional lift simulation mechanism comprises a first variable pitch ducted propeller 1 and a second variable pitch ducted propeller 2 which are identical in structure, rotation of the two propellers is respectively driven by two rotor DC speed reduction motors, pitch angles of the two propellers are driven by two pitch angle control stepping motors, a first rotating shaft 3 is arranged on the opposite surfaces of the two variable pitch ducted propellers, one end of the two first rotating shafts 3 is inserted into a cross arm 4, the cross arm 4 is connected with the swinging mechanism, the tail wing additional lift simulation mechanism comprises a first rolling wing 5 and a second rolling wing 6 which are identical in structure, the two rolling wings are arranged on a rolling wing bracket 7, a cross blade frame 23 is arranged at the front end and the rear end of the central shaft 22, four blades 24 are arranged on the two cross blade frames 23, a vertical blade 22 deflection mechanism 25 is arranged at the front end of the central shaft 22 and is used for realizing the deflection of the vertical blade 24, the vertical blade motor deflection mechanism is arranged on the stepping motor and controlled by the stepping motor, the speed reduction motor is controlled by the stepping motor, and the automatic steering motor is controlled by the stepping motor, and the speed reduction motor is controlled by a stepping motor, and the steering angle of the stepping motor is controlled by a stepping motor 29, and a steering angle controller 30 is connected with the stepping motor;
the aircraft additional lift simulation device of the embodiment further comprises a foot rudder, wherein the foot rudder is connected with an automatic controller through a host, the automatic controller drives a blade transverse deflection angle to control a stepping motor to work, the blade transverse deflection angle controls the stepping motor to control a biasing mechanism 25 to transversely act, and the automatic controller is a PLC or a singlechip;
The swing mechanism has the specific structure that: the swinging mechanism comprises a small cross-shaped connecting piece 8 and a large cross-shaped connecting piece 9, the small cross-shaped connecting piece 8 realizes the fixed connection of a cross arm 4 and a vertical shaft 10, the vertical shaft 10 passes through the large cross-shaped connecting piece 9 and then is connected with the head end of a rolling wing bracket 7 through a height adjusting mechanism, a speed damper 31 is arranged between the vertical shaft 10 and the large cross-shaped connecting piece 9, the large cross-shaped connecting piece 9 is arranged on a U-shaped support arm 12 through a transverse shaft 11, a vertical shaft 13 is arranged at the bottom of the U-shaped support arm 12, the bottom of the vertical shaft 13 is rotatably arranged on a supporting seat 17, pitching balance springs 14 are arranged at two ends of the transverse shaft 11 positioned at the outer side of the U-shaped support arm 12, the length direction of the pitching balance springs 14 is parallel to the height direction of the U-shaped support arm 12, a first U-shaped plug 15 capable of adjusting the position up and down is arranged at the bottom of the vertical shaft 13, a yaw balance spring 16 is parallel to the vertical shaft 10, and a second U-shaped plug 18 capable of adjusting the distance relative to the vertical shaft 13 is arranged on the upper surface of the supporting seat 17;
the height adjusting mechanism has the specific structure: the height adjusting mechanism comprises a height adjusting block 19 connected with the longitudinal shaft 10, a height adjusting plate 20 is inserted in the height adjusting block 19, two rows of height adjusting holes 32 are formed along the height direction of the height adjusting block 19, the height adjusting plate 20 is provided with two rows of height adjusting holes with the same width, and the height adjusting plate 20 is connected with the rolling wing bracket 7 through a connecting plate 21.
The biasing mechanism has the specific structure: the biasing mechanism 25 comprises a biasing ring 26 and four cross-shaped biasing rods 27 arranged on the outer circumference of the biasing ring 26, the biasing ring 26 is sleeved on a biasing shaft 28, and one end of each biasing rod 27 is hinged to the corresponding blade 24.
The control method of the aircraft additional lift simulation device of the embodiment comprises the following steps:
1. Simulating aircraft roll
When the control rod presses the right, the stepping motor is controlled by the two pitch angles to deflect the blades of the first variable-pitch ducted propeller 1 and the second variable-pitch ducted propeller 2 respectively, the leading edge of the blade of the first variable-pitch ducted propeller 1 deflects downwards to generate downward pulling force, and the leading edge of the blade of the second variable-pitch ducted propeller 2 deflects upwards to generate upward pulling force, so that the additional lift simulation device rolls right;
When the control rod presses the rod leftwards, the stepping motors are controlled by two pitch angles to respectively deflect the blades of the first variable-pitch ducted propeller 1 and the second variable-pitch ducted propeller 2, the leading edge of the blade of the first variable-pitch ducted propeller 1 deflects upwards to generate upward pulling force, and the leading edge of the blade of the second variable-pitch ducted propeller 2 deflects downwards to generate downward pulling force to enable the additional lift force simulation device to roll leftwards;
The speed damper 31 can restrict the rolling speed of the additional lift simulation device, so that the rolling angle speed of the additional lift simulation device is in direct proportion to the compression bar quantity of the control rod, and the rolling yaw moment can be generated by rotating the first rotating shaft 3 to enable the rear edges of the first variable-pitch ducted propeller 1 and the second variable-pitch ducted propeller 2 to deflect downwards, so that the simulation of the rolling yaw coupling effect of the aircraft is realized.
2. Simulating aircraft pitch
The two rolling wing direct current gear motors 30 drive the blade frames 23 of the first rolling wing 5 and the second rolling wing 6 to rotate at the same speed, the blades 24 do circular motion, when no manipulation is input, the rolling wings do not generate tensile force, the additional lift simulation device does not pitch, when the control rod pulls backwards, the two blade vertical deflection angles control the stepping motors 29 to respectively deflect the blades 24 of the first rolling wing 5 and the second rolling wing 6, and the front edges of the blades 24 of the first rolling wing 5 and the second rolling wing 6 deflect downwards to generate downward tensile force so as to enable the additional lift simulation device to tilt upwards;
When the operating lever pushes the rod forwards, the stepping motor 29 is controlled by the vertical deflection angles of the two paddles to deflect the paddles 24 of the first rolling wing 5 and the second rolling wing 6 respectively, and the front edges of the paddles 24 of the first rolling wing 5 and the second rolling wing 6 deflect upwards to generate upward pulling force so as to enable the additional lift simulation device to dip downwards;
Along with the pitching motion of the additional lift simulation device, the two pitching balance springs 14 deform, and when moment balance is formed between the two pitching balance springs and the tensile force generated by the two rolling wings, the additional lift simulation device is stabilized at a certain angle, so that the pitching control simulation of the aircraft is realized, and the pitching simulation of the aircraft with different pitching performances is realized by adjusting the high and low positions of the first U-shaped plug pins 15.
3. Simulation of aircraft yaw
The two rolling wing direct current speed reducing motors 30 drive the blade frames 23 of the first rolling wing 5 and the second rolling wing 6 to rotate at the same speed, when no manipulation is input, the rolling wings do not generate tensile force, the additional lift force simulation device does not yaw, when the right foot rudder is kicked, the stepping motors are controlled by the two blade transverse deflection angles to respectively deflect the blades 24 of the first rolling wing 5 and the second rolling wing 6, the front edges of the blades 24 of the first rolling wing 5 and the second rolling wing 6 deflect left to generate leftward tensile force, and the additional lift force simulation device yaw rightwards;
When a left foot rudder is kicked, the stepping motors are controlled through the transverse deflection angles of the two paddles to respectively deflect the paddles 24 of the first rolling wing 5 and the second rolling wing 6, and the front edges of the paddles 24 of the first rolling wing 5 and the second rolling wing 6 deflect right to generate rightward pulling force so as to enable the additional lift force simulation device to yaw leftwards;
Along with the yaw movement of the additional lift simulation device, the two yaw balance springs 16 deform, when the moment formed by the tensile force generated by the two rolling wings is balanced, the additional lift simulation device is stabilized at a certain angle, the yaw control simulation of the aircraft is realized, the yaw rolling moment can be generated by adjusting the installation height of the additional lift simulation mechanism of the tail wing, the simulation of the yaw rolling coupling effect of the aircraft is realized, and the yaw simulation of the aircraft with different yaw performances is realized by adjusting the far and near positions of the second U-shaped plug 18.
The additional lift simulation device provided by the invention provides a physical framework, can simulate the flight state and the maneuvering control of a special-condition airplane, finish maneuvering training beyond program exercise, and strengthen the undescribeable skills in the driving technology.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (3)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111586132.3A CN114049814B (en) | 2021-12-23 | 2021-12-23 | Aircraft additional lift simulation device and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111586132.3A CN114049814B (en) | 2021-12-23 | 2021-12-23 | Aircraft additional lift simulation device and control method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114049814A CN114049814A (en) | 2022-02-15 |
| CN114049814B true CN114049814B (en) | 2024-11-12 |
Family
ID=80213325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111586132.3A Active CN114049814B (en) | 2021-12-23 | 2021-12-23 | Aircraft additional lift simulation device and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114049814B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118262594B (en) * | 2024-03-29 | 2025-04-11 | 上海华模科技有限公司 | A flight simulator for preventing abnormal posture |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN216412427U (en) * | 2021-12-23 | 2022-04-29 | 中国人民解放军海军航空大学 | Aircraft additional lift force simulation device |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010041326A1 (en) * | 2000-05-12 | 2001-11-15 | Zeier Bruce E. | Simulator for aircraft flight training |
| US6641086B2 (en) * | 2001-08-14 | 2003-11-04 | Northrop Grumman Corporation | System and method for controlling an aircraft |
| FR2943620B1 (en) * | 2009-03-27 | 2012-08-17 | Eurocopter France | METHOD AND DEVICE FOR OPTIMIZING THE OPERATING POINT OF PROPELLANT PROPELLERS PROVIDED ON EITHER OF THE FUSELAGE OF A GIRAVION |
| CN101643116B (en) * | 2009-08-03 | 2012-06-06 | 北京航空航天大学 | Tiltrotor controlled by double-propeller vertical duct |
| CN202855112U (en) * | 2012-10-15 | 2013-04-03 | 昆山航理机载设备有限公司 | Motor-human sense simulation control system motor of helicopter |
| CN205055430U (en) * | 2015-10-20 | 2016-03-02 | 中国人民解放军海军航空工程学院 | But differential steering's high mobility model propeller aircraft |
| CN211766286U (en) * | 2020-01-20 | 2020-10-27 | 长沙航空职业技术学院 | Vertical take-off and landing fixed wing aircraft with four-duct variable-pitch rotor wings |
| CN111710210B (en) * | 2020-06-12 | 2024-11-29 | 中国人民解放军海军航空大学岸防兵学院 | Aircraft attitude control simulation training device |
| CN213958313U (en) * | 2020-11-09 | 2021-08-13 | 西安双马茂晟航空科技有限责任公司 | Aircraft control simulation training experimental device |
| CN112722262B (en) * | 2021-01-19 | 2022-11-11 | 西北工业大学 | Power deflection wing vertical take-off and landing unmanned aerial vehicle and control method thereof |
-
2021
- 2021-12-23 CN CN202111586132.3A patent/CN114049814B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN216412427U (en) * | 2021-12-23 | 2022-04-29 | 中国人民解放军海军航空大学 | Aircraft additional lift force simulation device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114049814A (en) | 2022-02-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2607358C (en) | System for controlling flight direction | |
| US20110177748A1 (en) | Vtol model aircraft | |
| CN111301677A (en) | Hoverable eight-wing flapping-wing aircraft and flight control method thereof | |
| CN112141331B (en) | A miniature flapping wing that can achieve large deformation and high control torque | |
| JP2011502869A (en) | Single rotor model helicopter with improved balance characteristics | |
| CN114049814B (en) | Aircraft additional lift simulation device and control method thereof | |
| CN206288235U (en) | A kind of reclining device for tiltrotor aircraft | |
| CN104608918A (en) | Control mechanism of small double-rotor unmanned aerial vehicle and mounting structure of control mechanism | |
| CN204895843U (en) | Multiaxis aircraft | |
| CN114187805A (en) | Special flight training simulation system based on aerodynamic force and control method | |
| CN204916174U (en) | Variable -pitch rotor device and many rotor crafts | |
| CN101204991A (en) | Four channel row two-bladed helicopter | |
| CN111003164A (en) | Coaxial tilting three-rotor-blade helicopter | |
| CN211869691U (en) | Hoverable eight-wing flapping aircraft | |
| CN216412427U (en) | Aircraft additional lift force simulation device | |
| CN209591167U (en) | A linkage joystick for large fixed-wing aircraft simulator | |
| CN207938219U (en) | A kind of Helicopter Simulator emulation operating mechanism | |
| KR20060110241A (en) | Dragonfly type wing vehicle with two pairs of wings | |
| CN222247703U (en) | Bionic butterfly aircraft | |
| CN108639331A (en) | One kind is verted double-rotor aerobat | |
| CN202070153U (en) | Rotor drive device of coaxial dual-propeller model helicopter | |
| CN114187804B (en) | Aerodynamic force-based special flight training teaching aid and control method thereof | |
| CN109367773B (en) | Tilting mechanism with control surface | |
| KR200434323Y1 (en) | Dragonfly type wing vehicle with two pairs of wings | |
| CN110473445B (en) | Aircraft flight attitude simulation equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |