Method and system to assist conventional fixed-wing aircraft landing, without a runway
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0388638
(2010-07-16)
|
등록번호 |
US-8498761
(2013-07-30)
|
우선권정보 |
ES-200930562 (2009-08-05) |
국제출원번호 |
PCT/ES2010/000311
(2010-07-16)
|
§371/§102 date |
20120412
(20120412)
|
국제공개번호 |
WO2011/015679
(2011-02-10)
|
발명자
/ 주소 |
- Gómez Pérez, José Patricio
- Gómez Pérez, Ignacio
- Monteagudo López De Sabando, Antonio
|
출원인 / 주소 |
- Universidad Politecnica de Madrid
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
1 |
초록
▼
A system allows conventional, unprepared fixed-wing aircraft to land safely on very small, unprepared areas, enabling an aerodynamic capacitance in which the airplanes can fly in a controlled manner against coherent air current, being assisted by a combined system including both the air current cont
A system allows conventional, unprepared fixed-wing aircraft to land safely on very small, unprepared areas, enabling an aerodynamic capacitance in which the airplanes can fly in a controlled manner against coherent air current, being assisted by a combined system including both the air current control mechanisms and the automatic flight control system of the aircraft.
대표청구항
▼
1. A system to assist conventional fixed-wing aircraft landing without a runway, said system comprising: a) a not-on-board installation which comprises: air potential generating means for providing air in adjustable pressure and flow rate conditions to;laminar airflow generating means for generating
1. A system to assist conventional fixed-wing aircraft landing without a runway, said system comprising: a) a not-on-board installation which comprises: air potential generating means for providing air in adjustable pressure and flow rate conditions to;laminar airflow generating means for generating a laminar air current from the air supplied by the air potential generating means;airflow control means for controlling the air potential generating means and laminar airflow generating means to obtain a controlled laminar air current;communication means for communicating with the aircraft responsible for: communicating information about the conditions of the generated laminar air current to the flight control system of the aircraft;receiving information about the flight conditions on the approach of the aircraft from the flight control system of the aircraft and communicating the flight conditions to the airflow control means;trajectory generating means for calculating and providing the aircraft with a trajectory to be followed by the aircraft through the communication means to guide the aircraft to a collection area;aircraft collecting and immobilizing means responsible for immobilizing the aircraft in the collection area once the aircraft has reached said collection area; wherein the airflow control means in cooperation with the flight control system of the aircraft and with interaction logic are configured for obtaining the controlled laminar air current with suitable conditions to maintain airworthiness of the aircraft in real time, depending on its approach conditions, the conditions of the generated current and the calculation of the trajectory by control hardware housing the interaction logic; b) an installation on board the aircraft which in turn comprises: flight control system responsible for: receiving information about the conditions of the generated laminar air current and the trajectory to be followed by the aircraft from the not-on-board installation to reach the collection area;receiving the control strategy defining the control of the aircraft from the control hardware housing the interaction logic;controlling the aircraft depending on at least said received information;sending information about the flight conditions on the approach of the aircraft to the not-on-board installation;sending information about the flight conditions on the approach of the aircraft to computing means housing the interaction logic;c) interaction logic housed in control hardware, implemented in the form of control laws of control software, responsible for: coordinating a flight control sub-system and airflow control sub-system so that the sub-systems work together to control the aircraft;listing coordinated operation of the flight control system of the aircraft, the control system of the aircraft collecting and immobilizing means and the airflow control means;providing instructions which must be fulfilled by each of the control systems such that controlled and safe operation of the aircraft inside the air produced by the laminar air flow rate generating system is achieved. 2. The system according to claim 1, wherein the laminar airflow generating means comprise: a pooling chamber responsible for containing a specific volume of air in thermodynamic conditions provided by the air potential generating means;at least one purge valve responsible for relieving pressure of the pooling chamber when the purge valve is activated to obtain the thermodynamic conditions;at least one nozzle responsible for exchanging the thermodynamic conditions of the air contained in the pooling chamber with conditions necessary to form a laminar air current having a section suited to the aircraft;a plurality of horizontal guide blades and vertical guide blades responsible for varying the direction of the generated laminar air current to perform a lateral and vertical control of said air current, respectively. 3. The system according to claim 1, wherein the airflow control means comprise: sensor means responsible for obtaining the conditions of the laminar air current and the state of the air potential generating means and the laminar airflow generating means;control means configured for controlling the air potential generating means and the laminar airflow generating means depending on control signals;data processing means responsible for generating said control signals in real time, depending on the information supplied by the sensor means, in cooperation with the flight control system of the aircraft and with the interaction logic, depending on approach conditions and the trajectory calculation by the control hardware housing the interaction logic. 4. The system according to claim 1, wherein the aircraft collecting and immobilizing means comprise: a landing platform which can be lifted by an articulated mechanism;lifting means of the landing platform for lifting the landing platform and bringing the landing platform closer to the aircraft when the aircraft is in the collection area;fixing and anchoring device responsible for immobilizing the aircraft in the collection area;sensor means for establishing a position of the fixing and anchoring device and the position of the aircraft;control unit configured for controlling the lifting means of the landing platform and the actuation of the fixing and anchoring device, following a command generated by the interaction logic, in real time and in cooperation with the airflow control systems of the aircraft, depending on the position of the aircraft and on the conditions of the generated current. 5. The system according to claim 4, wherein the fixing and anchoring device comprises a battery of electromagnets arranged in the landing platform. 6. The system according to claim 5, wherein the fixing and anchoring device comprises a mechanical fixing of the landing gear of the aircraft. 7. The system according to claim 1, wherein the trajectory generating means comprise a first GPS unit in the not-on-board installation and data processing means configured for: receiving the GPS position from the first GPS unit;receiving the GPS position of the aircraft from a second on board GPS unit;receiving the altitude of the aircraft from an altimeter on board the aircraft;generating the trajectory depending on at least: readings from the first and second GPS units;a reading from the on board altimeter;a reading from the on board and not-on-board air sensors. 8. The system according to claim 1, comprising a platform responsible for supporting the not-on-board installation. 9. The system according to claim 1, wherein the installation on board the aircraft additionally comprises immobilizing and anchoring means compatible with the aircraft collecting and immobilizing means of the not-on-board installation to jointly immobilize the aircraft in the collection area. 10. The system according to claim 5, wherein the immobilizing and anchoring means of the installation on board the aircraft comprise: a landing gear compatible with the aircraft collecting and immobilizing means of the not-on-board installation;a battery of electromagnets geometrically compatible with the electromagnets of the aircraft collecting and immobilizing means of the not-on-board installation;a control unit responsible for controlling the intensity of the electric current powering the battery of electromagnets of the aircraft depending on the position of the aircraft during the guiding maneuver and on the control commands generated by the interaction logic. 11. A method to assist conventional fixed-wing aircraft landing without a runway, comprising: generating an adjustable laminar air current directed against forward movement of the aircraft by a not-on-board installation;calculating an approach and collection strategy of the aircraft in real time by interaction logic, in cooperation with the airflow control system and the aircraft control system;providing the definition of a trajectory which must be followed by the aircraft to be guided to the collection area to glide slope generating means in real time and adapting the trajectory to conditions of a maneuver by the interaction logic;providing a strategy which must be followed by a flight control system of the aircraft to be guided to the collection area to the on board installation in real time and adapting the strategy to the conditions of the maneuver by the interaction logic;obtaining approach conditions of the aircraft in the not-on-board installation, in the on board installation and in the interaction logic;controlling the laminar air current with suitable conditions to maintain airworthiness of the aircraft depending on approach conditions of the aircraft and on a result from executing the interaction logic;controlling the aircraft to follow a generated glide slope depending on the conditions of the laminar air current and on the result from executing the interaction logic;immobilizing the aircraft in the collection area once the aircraft has reached said collection area by aircraft collecting and immobilizing means.
이 특허에 인용된 특허 (1)
-
Corbett Marshall J. (East Northport NY), Laser illumination system for aircraft launch and landing system.
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