CA2587835A1 - Automatic velocity control system for aircraft - Google Patents
Automatic velocity control system for aircraft Download PDFInfo
- Publication number
- CA2587835A1 CA2587835A1 CA002587835A CA2587835A CA2587835A1 CA 2587835 A1 CA2587835 A1 CA 2587835A1 CA 002587835 A CA002587835 A CA 002587835A CA 2587835 A CA2587835 A CA 2587835A CA 2587835 A1 CA2587835 A1 CA 2587835A1
- Authority
- CA
- Canada
- Prior art keywords
- aircraft
- parameter
- error signal
- primary
- airspeed
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control; Arrangement thereof
- B64D31/02—Initiating means
- B64D31/06—Initiating means actuated automatically
- B64D31/08—Initiating means actuated automatically for keeping cruising speed constant
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/04—Control of altitude or depth
- G05D1/06—Rate of change of altitude or depth
- G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
- G05D1/0615—Rate of change of altitude or depth specially adapted for aircraft to counteract a perturbation, e.g. gust of wind
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Feedback Control In General (AREA)
- Control Of Velocity Or Acceleration (AREA)
Abstract
A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft.
A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.
A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.
Claims (16)
1. A flight control system for an aircraft, the system comprising:
means for receiving an input signal representing a selected value of a first parameter, the first parameter being one of the airspeed of the aircraft and inertial velocity of the aircraft;
a primary feedback loop for generating a primary error signal, the primary error signal being proportional to the difference between the selected value of the first parameter and a measured value of the first parameter; and a secondary feedback loop for generating a secondary error signal, the secondary error signal being proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, the second parameter being the other of the airspeed of the aircraft and inertial velocity of the aircraft;
wherein the primary error signal and the secondary error signal are summed to produce a velocity error signal;
wherein the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal, and wherein the actuator command signal is adapted to be used for operating devices on the aircraft to control the first parameter of the aircraft, such that the primary error signal is minimized.
means for receiving an input signal representing a selected value of a first parameter, the first parameter being one of the airspeed of the aircraft and inertial velocity of the aircraft;
a primary feedback loop for generating a primary error signal, the primary error signal being proportional to the difference between the selected value of the first parameter and a measured value of the first parameter; and a secondary feedback loop for generating a secondary error signal, the secondary error signal being proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, the second parameter being the other of the airspeed of the aircraft and inertial velocity of the aircraft;
wherein the primary error signal and the secondary error signal are summed to produce a velocity error signal;
wherein the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal, and wherein the actuator command signal is adapted to be used for operating devices on the aircraft to control the first parameter of the aircraft, such that the primary error signal is minimized.
2. The control system according to Claim 1, wherein the means for receiving the input signal are configured for receiving an input signal generated onboard the aircraft.
3. The control system according to Claim 1, wherein the means for receiving the input signal are configured for receiving an input signal generated remote from the aircraft.
4. The control system according to Claim 1, wherein the first parameter is the airspeed of the aircraft and the second parameter is the inertial velocity of the aircraft.
5. The control system according to Claim 1, wherein the first parameter is the inertial velocity of the aircraft and the second parameter is the airspeed of the aircraft.
6. The control system according to Claim 1, wherein the actuator command signal is adapted to be used for operating devices selected from the group consisting of throttles, rotor system controls, and nacelle position controls.
7. An aircraft, comprising:
propulsion means for propelling the aircraft;
at least one device configured for controlling a thrust output of the propulsion means; and a flight control system, comprising:
means for receiving an input signal representing a selected value of a first parameter, the first parameter being one of the airspeed of the aircraft and inertial velocity of the aircraft;
a primary feedback loop for generating a primary error signal, the primary error signal being proportional to the difference between the selected value of the first parameter and a measured value of the first parameter; and a secondary feedback loop for generating a secondary error signal, the secondary error signal being proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, the second parameter being the other of the airspeed of the aircraft and inertial velocity of the aircraft;
wherein the primary error signal and the secondary error signal are summed to produce a velocity error signal;
wherein the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal, and wherein the actuator command signal is used for operating the at least one device to control the first parameter of the aircraft, such that the primary error signal is minimized.
propulsion means for propelling the aircraft;
at least one device configured for controlling a thrust output of the propulsion means; and a flight control system, comprising:
means for receiving an input signal representing a selected value of a first parameter, the first parameter being one of the airspeed of the aircraft and inertial velocity of the aircraft;
a primary feedback loop for generating a primary error signal, the primary error signal being proportional to the difference between the selected value of the first parameter and a measured value of the first parameter; and a secondary feedback loop for generating a secondary error signal, the secondary error signal being proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, the second parameter being the other of the airspeed of the aircraft and inertial velocity of the aircraft;
wherein the primary error signal and the secondary error signal are summed to produce a velocity error signal;
wherein the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal, and wherein the actuator command signal is used for operating the at least one device to control the first parameter of the aircraft, such that the primary error signal is minimized.
8. The aircraft according to Claim 7, wherein the at least one device comprises at least one throttle.
9. The aircraft according to Claim 7, wherein the at least one device comprises at least one actuator for vectoring thrust.
10. The aircraft according to Claim 7, wherein the means for receiving the input signal are configured for receiving an input signal generated onboard the aircraft.
11. The aircraft according to Claim 7, wherein the means for receiving the input signal are configured for receiving an input signal generated remote from the aircraft.
12. The aircraft according to Claim 7, wherein the first parameter is the airspeed of the aircraft and the second parameter is the inertial velocity of the aircraft.
13. The aircraft according to Claim 7, wherein the first parameter is the inertial velocity of the aircraft and the second parameter is the airspeed of the aircraft.
14. A method for automatically controlling the flight of an aircraft, the method comprising:
a) inputting a signal representing a selected value of a first parameter, the first parameter being one of the airspeed of the aircraft and the inertial velocity of the aircraft;
b) generating a primary error signal by calculating the difference between the selected value of the first parameter and a measured value of the first parameter;
c) generating a secondary error signal by calculating the difference between the selected value of the first parameter and a measured value of a second parameter, the second parameter being the other of the airspeed of the aircraft and the inertial velocity of the aircraft;
d) generating a velocity error signal by summing the primary error signal and the secondary error signal;
e) generating an actuator command signal by summing the velocity error signal and an integrated value of the primary error signal; then f) operating devices on the aircraft to control the first parameter of the aircraft, such that the primary error signal is minimized.
a) inputting a signal representing a selected value of a first parameter, the first parameter being one of the airspeed of the aircraft and the inertial velocity of the aircraft;
b) generating a primary error signal by calculating the difference between the selected value of the first parameter and a measured value of the first parameter;
c) generating a secondary error signal by calculating the difference between the selected value of the first parameter and a measured value of a second parameter, the second parameter being the other of the airspeed of the aircraft and the inertial velocity of the aircraft;
d) generating a velocity error signal by summing the primary error signal and the secondary error signal;
e) generating an actuator command signal by summing the velocity error signal and an integrated value of the primary error signal; then f) operating devices on the aircraft to control the first parameter of the aircraft, such that the primary error signal is minimized.
15. The method according to Claim 14, wherein the first parameter is the airspeed of the aircraft and the second parameter is the inertial velocity of the aircraft.
16. The method according to Claim 14, wherein the first parameter is the inertial velocity of the aircraft and the second parameter is the airspeed of the aircraft.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/US2005/032375 WO2007032757A1 (en) | 2005-09-12 | 2005-09-12 | Automatic velocity control system for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2587835A1 true CA2587835A1 (en) | 2007-03-22 |
| CA2587835C CA2587835C (en) | 2010-02-16 |
Family
ID=37865237
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2587835A Active CA2587835C (en) | 2005-09-12 | 2005-09-12 | Automatic velocity control system for aircraft |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US7931238B2 (en) |
| EP (1) | EP1924492B1 (en) |
| JP (1) | JP4712092B2 (en) |
| CN (1) | CN100519337C (en) |
| AU (1) | AU2005336430A1 (en) |
| BR (1) | BRPI0516143A (en) |
| CA (1) | CA2587835C (en) |
| DE (1) | DE05796783T1 (en) |
| WO (1) | WO2007032757A1 (en) |
Families Citing this family (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7949440B2 (en) * | 2006-12-22 | 2011-05-24 | Embraer-Empresa Brasileira De Aeronautica S.A. | Aircraft cruise speed control |
| FR2911689B1 (en) * | 2007-01-19 | 2009-04-03 | Airbus Sas | METHOD AND DEVICE FOR CONTROLLING THE SPEED OF AN AIRCRAFT |
| FR2938085B1 (en) * | 2008-11-05 | 2010-12-03 | Airbus France | METHOD AND DEVICE FOR MITIGATING THE EFFECTS OF A TURBULENCE ON AN AIRCRAFT |
| CA2784615C (en) * | 2009-12-18 | 2017-03-28 | National Research Council Of Canada | Response mode for control system of piloted craft |
| ES2632175T3 (en) * | 2009-12-21 | 2017-09-11 | The Boeing Company | Calculation and display of the warning speed for control with thrust asymmetry |
| US8123175B2 (en) * | 2009-12-24 | 2012-02-28 | Spin Master Ltd. | Velocity feedback control system for a rotor of a toy helicopter |
| CN102092475A (en) * | 2010-12-30 | 2011-06-15 | 清华大学 | Landing automatic flameout system for unmanned helicopter |
| US9044543B2 (en) | 2012-07-17 | 2015-06-02 | Elwha Llc | Unmanned device utilization methods and systems |
| US9254363B2 (en) | 2012-07-17 | 2016-02-09 | Elwha Llc | Unmanned device interaction methods and systems |
| USD731394S1 (en) * | 2013-10-24 | 2015-06-09 | Bell Helicopter Textron Inc. | Tiltrotor aircraft with fixed engines |
| USD739335S1 (en) * | 2013-10-24 | 2015-09-22 | Bell Helicopter Textron Inc. | Tiltrotor aircraft with forward-swept wings |
| US9506945B2 (en) | 2014-06-10 | 2016-11-29 | Sikorsky Aircraft Corporation | Rotorcraft flight parameter estimation |
| US10112722B2 (en) | 2015-01-15 | 2018-10-30 | Unison Industries Llc | Power control for propeller-driven aircraft |
| GB2540183A (en) * | 2015-07-08 | 2017-01-11 | Airbus Operations Ltd | Braking control system for an aircraft |
| US9922282B2 (en) | 2015-07-21 | 2018-03-20 | Limitless Computing, Inc. | Automated readiness evaluation system (ARES) for use with an unmanned aircraft system (UAS) |
| US9889926B2 (en) * | 2015-11-23 | 2018-02-13 | Gulfstream Aerospace Corporation | Air vehicles and systems for preemptive turbulence mitigation |
| US10752339B2 (en) * | 2016-03-18 | 2020-08-25 | The Boeing Company | Customizing aircraft performance systems and methods |
| CN106444358B (en) * | 2016-10-25 | 2020-05-26 | 深圳市高巨创新科技开发有限公司 | Method and system for automatically adjusting PID (proportion integration differentiation) parameters of multi-rotor aircraft |
| US10040542B1 (en) * | 2017-02-07 | 2018-08-07 | Bell Helicopter Textron Inc. | System and method for stabilizing longitudinal acceleration of a rotorcraft |
| US10611463B2 (en) * | 2017-04-05 | 2020-04-07 | Textron Innovations Inc. | Rotorcraft fly-by-wire stabilization |
| CN108090253B (en) * | 2017-11-29 | 2019-02-26 | 中国直升机设计研究所 | A kind of helicopter digital air system air speed modification method |
| US11292606B1 (en) * | 2018-09-13 | 2022-04-05 | Rockwell Collins, Inc. | Systems and methods of airspeed control with dynamic asymmetric airspeed reference |
| US11507115B2 (en) | 2019-10-09 | 2022-11-22 | Wing Aviation Llc | Contingent use of commanded speed in lieu of sensed airspeed to inform flight control decisions |
| CN112061379B (en) * | 2020-09-08 | 2022-04-12 | 中国人民解放军海军工程大学 | Aircraft turning control method for measuring acceleration and providing damping |
| CN113741173A (en) * | 2021-09-01 | 2021-12-03 | 中国航空工业集团公司西安飞行自动控制研究所 | Control method for realizing TRC (TRC control Unit) response type of fly-by-wire helicopter |
Family Cites Families (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2948496A (en) * | 1957-01-09 | 1960-08-09 | Sperry Rand Corp | Speed controlling system for aircraft |
| US3840200A (en) * | 1973-03-19 | 1974-10-08 | Boeing Co | Turbulence compensated throttle control system |
| US4189119A (en) * | 1977-11-22 | 1980-02-19 | The Boeing Company | Turbulence compensated throttle control system |
| US4245805A (en) * | 1977-11-25 | 1981-01-20 | The Boeing Company | Turbulence compensated throttle control system for aircraft having throttle command signal path control means responsive to engine rating control and flare initiation |
| US4277041A (en) * | 1978-09-11 | 1981-07-07 | Lockheed Corporation | Aircraft cruise speed control system |
| US4422147A (en) * | 1980-09-08 | 1983-12-20 | The Boeing Company | Wind shear responsive turbulence compensated aircraft throttle control system |
| US4763266A (en) * | 1982-12-27 | 1988-08-09 | The Boeing Company | Aircraft flight command and display system |
| US4853861A (en) * | 1987-09-01 | 1989-08-01 | Flight Dynamics, Inc. | Windshear measurement system |
| JP3068313B2 (en) * | 1992-03-11 | 2000-07-24 | 三菱重工業株式会社 | Automatic flight control system |
| US5359888A (en) * | 1993-02-16 | 1994-11-01 | The B. F. Goodrich Company | Air turbulence and wind shear sensor |
| US5553812A (en) * | 1994-06-03 | 1996-09-10 | United Technologies Corporation | Inertial velocity command system |
| FR2747204B1 (en) * | 1996-04-05 | 1998-06-12 | Aerospatiale | DEVICE FOR MAINTAINING THE SPEED OF AN AIRCRAFT WITHIN A DETERMINED SPEED DOMAIN |
| US6076024A (en) * | 1998-04-29 | 2000-06-13 | Sikorsky Aircraft Corporation | Earth-referenced wind adjustment for hovering aircraft |
| US6298286B1 (en) * | 1999-12-17 | 2001-10-02 | Rockwell Collins | Method of preventing potentially hazardously misleading attitude data |
| DE10048780A1 (en) * | 2000-09-29 | 2002-04-18 | Bosch Gmbh Robert | Operational control in vehicle using independent sensor and control unit, employs delay ensuring sensor information readiness for read-in and processing |
| US6885917B2 (en) * | 2002-11-07 | 2005-04-26 | The Boeing Company | Enhanced flight control systems and methods for a jet powered tri-mode aircraft |
| US6898941B2 (en) * | 2003-06-16 | 2005-05-31 | Carrier Corporation | Supercritical pressure regulation of vapor compression system by regulation of expansion machine flowrate |
-
2005
- 2005-09-12 BR BRPI0516143-6A patent/BRPI0516143A/en not_active IP Right Cessation
- 2005-09-12 CN CNB2005800360241A patent/CN100519337C/en active Active
- 2005-09-12 CA CA2587835A patent/CA2587835C/en active Active
- 2005-09-12 US US12/064,476 patent/US7931238B2/en active Active
- 2005-09-12 DE DE05796783T patent/DE05796783T1/en active Pending
- 2005-09-12 JP JP2008529971A patent/JP4712092B2/en active Active
- 2005-09-12 WO PCT/US2005/032375 patent/WO2007032757A1/en active Application Filing
- 2005-09-12 EP EP05796783A patent/EP1924492B1/en active Active
- 2005-09-12 AU AU2005336430A patent/AU2005336430A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| US7931238B2 (en) | 2011-04-26 |
| AU2005336430A1 (en) | 2007-03-22 |
| CN100519337C (en) | 2009-07-29 |
| EP1924492A1 (en) | 2008-05-28 |
| DE05796783T1 (en) | 2008-11-06 |
| WO2007032757A1 (en) | 2007-03-22 |
| EP1924492B1 (en) | 2012-08-29 |
| CN101044055A (en) | 2007-09-26 |
| BRPI0516143A (en) | 2008-08-26 |
| CA2587835C (en) | 2010-02-16 |
| JP2009507704A (en) | 2009-02-26 |
| EP1924492A4 (en) | 2011-09-07 |
| US20080308682A1 (en) | 2008-12-18 |
| JP4712092B2 (en) | 2011-06-29 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request |