CN100363232C - Anti-bump device for passenger plane of civil aviation - Google Patents
Anti-bump device for passenger plane of civil aviation Download PDFInfo
- Publication number
- CN100363232C CN100363232C CNB200610080662XA CN200610080662A CN100363232C CN 100363232 C CN100363232 C CN 100363232C CN B200610080662X A CNB200610080662X A CN B200610080662XA CN 200610080662 A CN200610080662 A CN 200610080662A CN 100363232 C CN100363232 C CN 100363232C
- Authority
- CN
- China
- Prior art keywords
- cylinder
- air
- state
- gas flow
- pressure
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention discloses a bumping prevention device for a civil aviation passenger plane, which is characterized in that the present invention comprises a pneumatic sensor, ailerons with variable cross sections and a controller, wherein the pneumatic sensor is installed on the head part of a passenger plane and is used for checking the abrupt change state of air currents; the ailerons are symmetrically and respectively installed above plane wings on the left and the right sides; each of the ailerons with variable cross sections is composed of a fixed wing and a sliding wing; the front end of each of the sliding wings is inserted in each of the fixed wings; the controller controls an actuating mechanism of the ailerons according to the signal change of the pneumatic sensor; when air currents make a plane body descend, the controller controls the sliding wings to reduce the depth of the insertion of the sliding wings into the fixed wings through the actuating mechanism to increase the areas of the cross sections of the ailerons; when air currents make the plane body ascend, the controller controls the sliding wings to increase the depth of the insertion of the sliding wings into the fixed wings through the actuating mechanism to reduce the areas of the cross sections of the ailerons. The bumping prevention device for a civil aviation passenger plane can overcome or relieve bumping caused by the abrupt change of air currents.
Description
Technical field
The invention belongs to aerospace field, relate to a kind of device that airline carriers of passengers uses, is a kind of device of fuselage being jolted because of the atmosphere variations in flow of preventing specifically.
Background technology
Present airline carriers of passengers, owing to do not adopt the anti-measure of jolting,, can cause jolting of fuselage if therefore in flight course, run into the air-flow steep variation, the occupant is done not feel like oneself even cause frightened and meet accident, and brought inconvenience for people's journey life.
Summary of the invention
Purpose of the present invention is exactly at the problems referred to above, and a kind of device that can effectively prevent or alleviate aircraft big bump in flight course is provided, to improve the traveling comfort in the passenger traffic process.
In order to realize purpose of the present invention, the present invention adopts following technical scheme: a kind of anti-bump device for passenger plane of civil aviation, comprise that the pneumatic sensor that is installed in the passenger plane head is used to detect the steep variation state of air-flow, also comprise the variable cross section aileron that is installed in wing top, the left and right sides symmetrically respectively, the variable cross section aileron is made up of the sliding closure that fixed-wing and front end are inserted in the fixed-wing, and controller, described controller changes the actuating unit of control aileron according to the signal of pneumatic sensor, when air-flow descends fuselage, controller reduces its degree of depth of inserting fixed-wing by the actuating mechanism controls sliding closure and increases the aileron sectional area, and controller increases the sectional area that its degree of depth of inserting fixed-wing reduces aileron by the actuating mechanism controls sliding closure when air-flow rises fuselage.
Described pneumatic sensor, comprise a gas flow tube that can flow through air-flow, the gas flow tube axis is parallel with axes of aircraft, at the gas flow tube front end is admission port, a state of flight simulator that has same or similar flight characteristics with passenger plane is arranged in the gas flow tube, the upper position that gas flow tube is positioned at the state of flight simulator be equipped with vertical with gas flow tube on pressure nozzle, a last pressure-sensitive elastic membrane periphery that is positioned at pressure nozzle is fixed on the pressure nozzle inwall, state of flight simulator top is connected with one and uploads depression bar, upload the depression bar upper end and be fixed on the described pressure-sensitive elastic membrane center of going up, last induction tube top communicates with ambient atmosphere, last pressure-sensitive elastic membrane bottom is a upper chamber, and this air chamber communicates with gas flow tube by last pore and keeps equilibrium of pressure; The lower position that is positioned at the state of flight simulator in gas flow tube has following pressure nozzle, be positioned on the fixing pressure nozzle inwall down of following pressure-sensitive elastic membrane periphery of following pressure nozzle, state of flight simulator below is connected with a following pressure transmission bar, following pressure transmission bar lower end is fixed on down pressure-sensitive elastic membrane center, following induction tube below communicates with ambient atmosphere, following pressure-sensitive elastic membrane top is a lower chamber, and this air chamber communicates with gas flow tube by following pore and keeps equilibrium of pressure; There is servomotor control state of flight simulator to change sectional area in the state of flight simulator; Pick up camera is installed in gas flow tube takes the state of state of flight simulation, and its speed, direction and acceleration information be transferred to described controller, the servomotor that controller is controlled in the described state of flight simulator maintains on the gas flow tube axis state of flight simulator under normal condition.
Described actuating unit can be air-actuator, comprise the solenoid directional control valve on a cylinder and the cylinder inlet and outlet pipeline, parts in these two parts of the cylinder barrel of cylinder and piston rod are fixed, another parts are consistent with the direction of slip of described sliding closure connection and its sense of motion and sliding closure, and described electromagnetic valve is connected with described controller and is used to make cylinder operation by its control.
The present invention is by increasing variable cross section aileron and pneumatic sensor, controller formation state of flight setting device, record the variations in flow signal that causes air craft battery by pneumatic sensor, change its sectional area by controller control aileron, adjust airplane ascensional force to overcome or to alleviate owing to jolting that the air-flow steep variation causes.
Description of drawings
Fig. 1 is an anti-bump device for passenger plane of civil aviation layout of the present invention.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is a variable cross section aileron partial schematic sectional view.
Fig. 4 is the birds-eye view of Fig. 3.
Fig. 5 is the air-actuator pining drawing.
Fig. 6 is the pneumatic sensor structural representation.
The specific embodiment
Below in conjunction with the drawings and specific embodiments anti-bump device for passenger plane of civil aviation of the present invention is described further, to help understanding content of the present invention.
As depicted in figs. 1 and 2, anti-bump device for passenger plane of civil aviation, comprise the pneumatic sensor 1 that is installed in passenger plane head front end radome 4 belows and be installed in the interior controller (omitting among the figure) of fuselage, as shown in Figure 5, controller can adopt a computing machine 28, also comprise the symmetrical respectively a pair of variable cross section aileron 3 that is installed in wing top, the left and right sides, variable cross section aileron 3 is positioned at the driving engine top, make it in flight course, change sectional area by controller control according to state of flight, to adjust airplane ascensional force, offset the lift variation that unstable air-flow causes.Power lead and signal wire (SW) 6 are positioned at fuselage.
As shown in Figure 3 and Figure 4, the variable cross section aileron is made up of the sliding closure 8 that a fixed-wing 7 and front end are inserted in the fixed-wing 7, constitutes telescopic wing, and the cross sectional shape of fixed-wing 7 and sliding closure 8 designs according to existing aircraft airfoil section, to obtain lift.Control sliding closure 8 insert in the fixed-wings 7 the degree of depth can change the sectional area of whole aileron, obtain different lift.Under the aircraft average flight state, simultaneously with reference to shown in Figure 5, computing machine 28 as controller can change the actuating unit of controlling aileron according to the signal that causes air craft battery that pneumatic sensor obtained, when air-flow descends fuselage, controller reduces the sectional area that its degree of depth of inserting fixed-wing 7 increases aileron by actuating mechanism controls sliding closure 8, and controller increases the sectional area that its degree of depth of inserting fixed-wing 7 reduces aileron by actuating mechanism controls sliding closure 8 when air-flow rises fuselage.
Be understandable that, actuating unit for driving the aileron variable section can be motor drive mechanism, for example by on sliding closure 8 tooth bar being set, by the engagement of the wheel and rack on the motor output shaft, utilize the control motor positive and inverse and rotate the number of turns or angle realization aileron variable section.Perhaps adopt hydraulic actuating cylinder, drive sliding closure 8 and slide.According to the characteristics of airline carriers of passengers, and the fireballing characteristics of variations in flow that cause air craft battery, reaction that the present invention is preferred is air-actuator more rapidly.
Air-actuator structure such as Fig. 3 and shown in Figure 5, air-actuator 5 and aileron are fixed on the aero-engine hanger 2 by bracing frame 13 usefulness riveting bolts.Air-actuator is made of cylinder and solenoid directional control valve.For the cylinder bar mode fixing with respect to aircraft, adopt fixed-wing 7 to utilize attachment pegs 9 hinged with the cylinder bar 10 of cylinder, 8 of sliding closures are fastened on by its slip pipe 12 on the cylinder barrel 11 of cylinder.As shown in Figure 5, the electromagnetic valve 29 of solenoid directional control valve is controlled by the computing machine 28 as controller, realizes the commutation of cylinder gas circuit.Adopt another advantage of air-actuator to be, high pressure air in the high-pressure pipe 31 that links to each other with solenoid directional control valve can derive from the air compressor of the jet engine of aircraft, Hydraulic Station when having reduced air compressor or having adopted hydraulic actuating cylinder, simplify the structure and reduced cost, be convenient to mounting arrangement more.As shown in Figure 5, the right adapting pipe 32 of cylinder communicates with the preceding cavity of cylinder barrel 11, and the Left-wing Federation takes over 33 and is communicated with by the rear chamber of air flue with cylinder barrel 11, and the freeing pipe 34 that communicates with solenoid directional control valve is used for exhaust.Under the control of computing machine 28, by electromagnetic switch valve core 30 moving and to the right, realize the commutation of cylinder gas circuit left, the cylinder barrel 11 of cylinder is moved forward or backward, so that sliding closure 8 moves linearly forward and backward.
Pneumatic sensor can be used to measure the flow velocity or the pressure changing of the air-flow that causes air craft battery, yet this sensor can increase the control difficulty.As shown in Figure 6, pneumatic sensor of the present invention has adopted a kind of special construction, comprise a gas flow tube 14 that air flow stream is crossed, the axial line of gas flow tube 14 and aircraft axis parallel, gas flow tube 14 front ends are admission port, a variable cross section state of flight simulator 15 that has identical flight characteristics with passenger plane is arranged in gas flow tube 14, and state of flight simulator 15 can adopt the slip variable section structure identical with aileron.It is suitable substantially with the flight characteristics of aircraft that state of flight simulator 15 will guarantee it by wind tunnel experiment.The upper position that is positioned at state of flight simulator 15 on the gas flow tube 14 be equipped with vertical with gas flow tube on pressure nozzle 20, last pressure-sensitive elastic membrane 19 peripheries that are positioned at pressure nozzle 20 are fixed on the inwall of pressure nozzle 20, make pressure nozzle 20 be isolated into upper and lower two parts, its top communicates with extraneous air-flow, the bottom is formed with a upper chamber, and by last pore 26 balance that keep-ups pressure that communicates with gas flow tube 14, state of flight simulator top is connected with one and uploads depression bar 17, uploads depression bar 17 upper ends and is fixed on pressure-sensitive elastic membrane 19 centers; The lower position that is positioned at state of flight simulator 15 in gas flow tube 14 has following pressure nozzle 22, being positioned at down, following pressure-sensitive elastic membrane 21 peripheries of pressure nozzle 22 are fixed on down on the inwall of pressure nozzle 22, to descend pressure nozzle 22 to be divided into two parts up and down equally, there is lower chamber on its top by following pore 27 and gas flow tube 14 balance that keep-ups pressure, the bottom then communicates with extraneous air-flow, state of flight simulator 15 belows are connected with a following pressure transmission bar 18, and following pressure transmission bar 18 lower ends are fixed on down the center of pressure-sensitive elastic membrane 21; There are servomotor 16 control state of flight simulators 15 to change sectional area in the state of flight simulator; Pod apertures 25 is arranged so that air-flow is derived on the gas flow tube 14, pick up camera 23 is installed in gas flow tube 14 takes state of flight simulator 15 change in location situations, and speed, direction and acceleration information that state of flight simulator 15 changes be transferred to computing machine 28 as controller, adjust aileron by computing machine 28 according to the situation of change of state of flight simulator.Connection line 24 between computing machine 28 and the servomotor 16 passes by uploading in the depression bar 18.Adopt air chamber structure in last pressure nozzle and the following pressure nozzle, form dumping force to prevent aircraft when the high-speed flight, the air-flow of formation disturbance and the negative pressure of generation make two pressure-sensitive elastic membranes move the vibration that causes to the middle part in the gas flow tube.
Its principle of work is: because pneumatic sensor 1 is installed in aircraft foremost, so when aircraft ran into unstable air-flow, it can be reacted in advance.With reference to shown in Figure 5, because state of flight simulator 15 has basic identical or similar flight characteristics to aircraft, when aircraft flew on normal height with the predetermined speed of a ship or plane, if there is not unstable air-flow, state of flight simulator 15 should be still on the axis of gas flow tube 14.As the flight parameter people of aircraft for a change the time, the axis that gas flow tube 14 will be departed from state of flight simulator 15 residing positions (highly), in this case, the pick up camera 23 that is installed in the gas flow tube 14 can send the situation that departs from of state of flight simulator 15 to control computer 28, control computer 28 can be according to departing from situation, control the micro servo motor 16 that is installed in the state of flight simulator 15 by circuit 24, adjust the area of state of flight simulator, thereby make on its axis that is positioned at gas flow tube 14 all the time.
If the subtend horizontal gas flow of aircraft sharply strengthens or when running into strong up current, state of flight simulator 15 will move up under the effect that horizontal gas flow strengthens or under the promotion in pressure-sensitive elastic membrane 21 down.This moment, pick up camera 23 meetings were given control computer 28 with information transfer such as its speed that moves up and height and acceleration/accels, the latter can control solenoid directional control valve 29 according to these information, so that spool 30 moves right by preset program, thereby make high-pressure pipe 31 and right adapting pipe 32 UNICOMs, the high pressure airs in the high-pressure pipe 31 derive from the air compressor of the jet engine of aircraft.After high-pressure pipe 31 and right adapting pipe 32 UNICOMs, high pressure air will enter the front portion of cylinder barrel 11 by the downtake 36 of cylinder bar 10, promptly in the left chamber of piston 35, thereby cylinder barrel 11 is moved to the left under the effect of high pressure air; Meanwhile, moving right of spool 30 makes Left-wing Federation's adapter 33 and freeing pipe 34 UNICOMs, after both UNICOMs, in the cylinder barrel 11, the air that is positioned at piston 35 right chamber can take over 33 through the last air flue 37 and the Left-wing Federation of cylinder bar 10, and is discharged by freeing pipe 34 by spool 30.As shown in Figure 3 and Figure 4, because the sliding closure 8 of aileron is fastened on the cylinder barrel 11, so when cylinder barrel 11 is moved to the left, sliding closure 8 can be moved to the left thereupon, thereby dwindled the whole sectional area of aileron, consequently reduced the lift of aircraft, offset the increase of subtend air-flow or gone up and risen the lift that stream is produced, and then effectively controlled jolting of aircraft.
And when the subtend air-flow of aircraft sharply weakened or runs into strong down gust, state of flight simulator 15 will move down under the effect of subtend airflow drops or under the pressure of last pressure-sensitive elastic membrane 19.This moment, pick up camera 23 meetings were with information such as its speed that moves down and height and acceleration/accels, be transferred to control computer 28, the latter can control electromagnetic valve 29 according to these information, so that spool 30 is moved to the left by predetermined and program, thereby make the high-pressure pipe 31 and the Left-wing Federation take over 33 UNICOMs, after the UNICOM, high pressure air in the high-pressure pipe 31 will enter the rear portion of cylinder barrel 11 by the last air flue 37 of cylinder bar 10, it is the right side of piston 35, thereby cylinder barrel 11 is moved right under the effect of high pressure air, meanwhile, being moved to the left of spool 30 makes right adapting pipe 32 and freeing pipe 34 UNICOMs, after both UNICOMs, in the cylinder barrel 11, the air that is positioned at piston 35 left sides can be through the downtake 36 and the right adapting pipe 32 of cylinder bar 10, and is discharged by freeing pipe 34 by spool 30.As shown in Figure 3 and Figure 4, because the sliding closure 8 of aileron is fastened on the cylinder barrel 11, so when cylinder barrel 11 moves right, sliding closure 8 can move right thereupon, thereby increased the area of aileron, consequently strengthened the lift of aircraft, offset the lift that the subtend horizontal gas flow weakens or down gust causes and descended, and then effectively controlled jolting of aircraft.
Claims (10)
1. anti-bump device for passenger plane of civil aviation, it is characterized in that: comprise that the pneumatic sensor that is installed in the passenger plane head is used to detect the steep variation state of air-flow, also comprise the variable cross section aileron that is installed in wing top, the left and right sides symmetrically respectively, the variable cross section aileron is made up of the sliding closure that fixed-wing and front end are inserted in the fixed-wing, and controller, described controller changes the actuating unit of control aileron according to the signal of pneumatic sensor, when air-flow descends fuselage, controller reduces its degree of depth of inserting fixed-wing by the actuating mechanism controls sliding closure and increases the aileron sectional area, and controller increases the sectional area that its degree of depth of inserting fixed-wing reduces aileron by the actuating mechanism controls sliding closure when air-flow rises fuselage.
2. anti-bump device for passenger plane of civil aviation as claimed in claim 1, it is characterized in that: described pneumatic sensor, comprise a gas flow tube that can flow through air-flow, the gas flow tube axis is parallel with axes of aircraft, at the gas flow tube front end is admission port, state of flight mould device with identical slip variable section structure with the passenger plane aileron is arranged in the gas flow tube, the upper position that gas flow tube is positioned at the state of flight simulator be equipped with vertical with gas flow tube on pressure nozzle, a last pressure-sensitive elastic membrane periphery that is positioned at pressure nozzle is fixed on the pressure nozzle inwall, state of flight simulator top is connected with one and uploads depression bar, upload the depression bar upper end and be fixed on the described pressure-sensitive elastic membrane center of going up, last induction tube top communicates with ambient atmosphere, last pressure-sensitive elastic membrane bottom is a upper chamber, and this air chamber communicates with gas flow tube by last pore and keeps equilibrium of pressure; The lower position that is positioned at the state of flight simulator in gas flow tube has following pressure nozzle, being positioned at down, a following pressure-sensitive elastic membrane periphery of pressure nozzle is fixed on down on the pressure nozzle inwall, state of flight simulator below is connected with a following pressure transmission bar, following pressure transmission bar lower end is fixed on down pressure-sensitive elastic membrane center, following induction tube below communicates with ambient atmosphere, following pressure-sensitive elastic membrane top is a lower chamber, and this air chamber communicates with gas flow tube by following pore and keeps equilibrium of pressure; There is servomotor control state of flight simulator to change sectional area in the state of flight simulator; Pick up camera is installed in gas flow tube takes the state of state of flight simulation, and its speed, direction and acceleration information be transferred to described controller, the servomotor that controller is controlled in the described state of flight simulator maintains on the gas flow tube axis state of flight simulator under normal condition.
3. anti-bump device for passenger plane of civil aviation as claimed in claim 2 is characterized in that: the connection line between described controller and the described servomotor is passed by described uploading in the depression bar.
4. as described anti-bump device for passenger plane of civil aviation one of in the claim 1 to 3, it is characterized in that: described actuating unit is an air-actuator.
5. anti-bump device for passenger plane of civil aviation as claimed in claim 4, it is characterized in that: described air-actuator comprises the solenoid directional control valve on a cylinder and the cylinder inlet and outlet pipeline, there are parts to fix in these two parts of the cylinder barrel of cylinder and piston rod, another parts are consistent with the direction of slip of described sliding closure connection and its sense of motion and sliding closure, and described electromagnetic valve is connected with described controller and is used to make cylinder operation by its control.
6. anti-bump device for passenger plane of civil aviation as claimed in claim 5 is characterized in that: the cylinder bar of described fixed-wing and described cylinder is hinged, and the cylinder barrel of described sliding closure and cylinder is hinged.
7. anti-bump device for passenger plane of civil aviation as claimed in claim 6 is characterized in that: described sliding closure is fastened on the cylinder barrel of cylinder by slip pipe.
8. anti-bump device for passenger plane of civil aviation as claimed in claim 6 is characterized in that: have last air flue and downtake to communicate with the chamber of cylinder piston both sides respectively in the cylinder bar of described cylinder.
9. anti-bump device for passenger plane of civil aviation as claimed in claim 5 is characterized in that: the source of the gas of described cylinder derives from the air compressor of the jet engine of aircraft.
10. anti-bump device for passenger plane of civil aviation as claimed in claim 4 is characterized in that: described air-actuator and aileron are fixed on the hanger of aero-engine with the riveting bolt by bracing frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200610080662XA CN100363232C (en) | 2006-05-25 | 2006-05-25 | Anti-bump device for passenger plane of civil aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200610080662XA CN100363232C (en) | 2006-05-25 | 2006-05-25 | Anti-bump device for passenger plane of civil aviation |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1843846A CN1843846A (en) | 2006-10-11 |
| CN100363232C true CN100363232C (en) | 2008-01-23 |
Family
ID=37062820
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB200610080662XA Expired - Fee Related CN100363232C (en) | 2006-05-25 | 2006-05-25 | Anti-bump device for passenger plane of civil aviation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100363232C (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105185166A (en) * | 2015-09-10 | 2015-12-23 | 杨建疆 | Unmanned aircraft city air control system |
| CN108313313A (en) * | 2018-01-26 | 2018-07-24 | 重庆邮电大学 | Unmanned plane failure response system |
| CN111968415A (en) * | 2020-08-27 | 2020-11-20 | 中国商用飞机有限责任公司 | System and method for prompting air bump of airplane |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3516998C2 (en) * | 1985-05-10 | 1988-09-08 | Ralf 4020 Mettmann De Lorsbach | |
| DE4205156A1 (en) * | 1992-02-20 | 1992-07-30 | Ludwig Scholz | Variable section wing for hang-glider - has two separate lift surfaces for high and low speed flight |
| CN2345452Y (en) * | 1998-07-16 | 1999-10-27 | 孙卫东 | Airplane with retractable wing |
-
2006
- 2006-05-25 CN CNB200610080662XA patent/CN100363232C/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3516998C2 (en) * | 1985-05-10 | 1988-09-08 | Ralf 4020 Mettmann De Lorsbach | |
| DE4205156A1 (en) * | 1992-02-20 | 1992-07-30 | Ludwig Scholz | Variable section wing for hang-glider - has two separate lift surfaces for high and low speed flight |
| CN2345452Y (en) * | 1998-07-16 | 1999-10-27 | 孙卫东 | Airplane with retractable wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1843846A (en) | 2006-10-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108298064B (en) | Unconventional yaw control system | |
| US7316371B2 (en) | Method and device for steepening a landing approach of an aircraft | |
| WO2016184358A1 (en) | Fixed structure type vertical take-off and landing aircraft based on dual flying control systems and control method therefor | |
| CN109711008A (en) | A kind of center of gravity of airplane envelope curve calculation method | |
| CN108725777B (en) | Amphibious unmanned aerial vehicle based on ducted vector propulsion | |
| US20070170309A1 (en) | Flight device (aircraft) with a lift-generating fuselage | |
| CN102356024A (en) | An aircraft comprising a device for influencing the directional stability of the aircraft, and a method for influencing the directional stability of the aircraft | |
| CN104787306A (en) | Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force | |
| WO1995011159A1 (en) | Aircraft flight control system | |
| CN100363232C (en) | Anti-bump device for passenger plane of civil aviation | |
| CN103204238A (en) | Jet rudder surface control system, aircraft using same, and method for controlling aircraft | |
| JP4534018B2 (en) | Flying machine | |
| CN100358776C (en) | Miniature airplane pitch operating method and control mechanism | |
| CN101758865A (en) | Inflatable automobile | |
| CN102085911A (en) | Novel flight and aircraft | |
| CN113911343B (en) | High-efficiency transmission flapping wing mechanism with rolling control function | |
| JP2022530223A (en) | Vertical takeoff and landing aircraft, and related control methods | |
| CN118124454A (en) | Balance adjusting device and balance adjusting system of aerocar cabin | |
| CN205256672U (en) | Manpower drive fixed -wing aircraft | |
| CN113232840B (en) | Tail-sitting vertical type vertical take-off and landing aircraft adopting series-parallel landing gear | |
| CN203294308U (en) | Jet rudder control system and aircraft using control system | |
| JP2004026034A (en) | Vertical takeoff and landing aircraft | |
| CN206265289U (en) | A kind of aircraft pitch, rollover, yaw control system | |
| CN2928681Y (en) | Wing surface jet vortex flapping wing aircraft | |
| CN208715466U (en) | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080123 |