FR2906525A1 - Electronic telemetry device for e.g. minidrone, has controller triggering nose up of non-piloted aircraft along angle predetermined by action on its control surfaces for receiving unique command in all or nothing mode from detecting unit - Google Patents
Electronic telemetry device for e.g. minidrone, has controller triggering nose up of non-piloted aircraft along angle predetermined by action on its control surfaces for receiving unique command in all or nothing mode from detecting unit Download PDFInfo
- Publication number
- FR2906525A1 FR2906525A1 FR0608714A FR0608714A FR2906525A1 FR 2906525 A1 FR2906525 A1 FR 2906525A1 FR 0608714 A FR0608714 A FR 0608714A FR 0608714 A FR0608714 A FR 0608714A FR 2906525 A1 FR2906525 A1 FR 2906525A1
- Authority
- FR
- France
- Prior art keywords
- ground
- aircraft
- telemetry device
- electronic telemetry
- electronic
- 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.)
- Pending
Links
- 108091008695 photoreceptors Proteins 0.000 claims description 4
- 230000005693 optoelectronics Effects 0.000 claims description 2
- 238000001514 detection method Methods 0.000 claims 1
- 238000000034 method Methods 0.000 description 3
- 210000001015 abdomen Anatomy 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 238000002604 ultrasonography Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000008685 targeting Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/60—Take-off or landing of UAVs from a runway using their own power
-
- 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
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
Description
Les aéronefs pilotés disposent de moyens d'atterrissage manuels ouManned aircraft have manual landing gear or
automatiques sophistiqués. Dans le cas d'aéronefs sans pilote, l'atterrissage est rendu plus délicat. C'est le cas en particulier pour les minidrones, petits aéronefs sans pilote, servant à l'observation de lieux difficilement accessibles, accomplissant des missions automatiques ou pilotées par télécommande à partir du sol, qui doivent être ramenés au 6 sol et récupérés en bon état après l'exécution de leur mission d'observation. En aéromodélisme, la phase d'atterrissage est très délicate et demande de la part du pilote au sol un entraînement acquis au cours de nombreuses heures de vol pour être réussie, et lui permettre de maîtriser cette procédure. sophisticated automatic. In the case of unmanned aircraft, the landing is made more difficult. This is particularly the case for minidrones, small unmanned aircraft, used to observe inaccessible places, performing automatic or remote-controlled missions from the ground, which must be returned to the ground and recovered in good condition. state after the execution of their observation mission. In model aircraft, the landing phase is very delicate and requires the pilot on the ground training acquired during many hours of flight to be successful, and allow him to master this procedure.
12 Il existe différents dispositifs qui utilisent des modules télémétriques orientés vers le sol, des liaisons par satellite, des ondes ultrasonores, ou encore des procédés à visée laser. Leur mise en oeuvre est complexe et onéreuse. De plus, la précision obtenue peut varier en fonction des conditions extérieures et de l'environnement. La phase d'atterrissage, qui consiste à cabrer l'aéronef, doit être exécutée à un instant qui requiert une grande précision.There are various devices that use ground-oriented telemetry modules, satellite links, ultrasonic waves, or laser targeting methods. Their implementation is complex and expensive. In addition, the accuracy obtained may vary depending on the external conditions and the environment. The landing phase, which consists of pitching the aircraft, must be executed at a time that requires great precision.
18 Considérant ces difficultés, l'invention a été conçue pour permettre l'atterrissage autonome et en toute sécurité d'aéronefs sans pilote, et pour être d'une mise en oeuvre simple, et d'un coût peu élevé. Elle permet d'équiper entre autres, et avec une bonne sécurité les minidrones de reconnaissance ou d'observation.Considering these difficulties, the invention has been designed to allow the autonomous and safe landing of unmanned aircraft, and to be simple to implement, and at a low cost. It allows to equip among others, and with a good security the minidrones of recognition or observation.
24 Le présent dispositif a pour objectif de permettre le retour au sol de ces aéronefs sans pilote, en totale autonomie, sans dépendre d'aucune variable ni intervention extérieures. Selon l'invention, lorsque l'aéronef est placé sur une trajectoire choisie, à une altitude basse, une unique impulsion de commande radioguidée est émise par le pilote au sol. Cette action réalise quatre opérations quasi-simultanées en mode automatique : (a) la libération et la mise en place d'un capteur d'information qui peut, selon l'invention, être 30 de nature mécanique ayant la forme générale d'une tige, située sous le ventre de l'aéronef, qui se positionne en direction du sol, ou bien d'un autre système de télémétrie tel que optique utilisant une diode laser d'émission et un photorécepteur, ou à ultrasons ; (b) l'action positionne l'aéronef en léger piqué ; (c) elle coupe le moteur de propulsion ; (d) elle sort les volets d'aérofreins. Ce système de télémétrie d'approche autorise une précision constante et fiable, tout en étant d'une mise en oeuvre très simple.24 The purpose of this device is to allow these unmanned aircraft to return to the ground in complete autonomy, without depending on any outside variables or intervention. According to the invention, when the aircraft is placed on a chosen trajectory, at a low altitude, a single radio-controlled command pulse is emitted by the pilot on the ground. This action performs four almost simultaneous operations in automatic mode: (a) the release and the installation of an information sensor which can, according to the invention, be of a mechanical nature having the general shape of a rod located under the belly of the aircraft, which is positioned in the direction of the ground, or of another telemetry system such as optical using a laser diode emission and a photoreceptor, or ultrasound; (b) the action positions the aircraft in a slight dive; (c) it cuts the propulsion motor; (d) She takes out the airbrake flaps. This approach telemetry system allows a constant and reliable accuracy, while being a very simple implementation.
36 42 48 1 2906525 Un calculateur miniaturisé (1) embarqué sur l'aéronef prend ces quatre commandes en charge à réception de l'ordre unique reçu du pilote au sol. L'aéronef poursuit alors sa descente, jusqu'au moment où la tige (2) vient à toucher le sol, ou bien ou le photorécepteur reçoit la réflexion du signal émis par la diode laser (figure 5), ou encore que le dispositif à ultra-sons reçoit un signal réfléchi par le sol à courte distance (figure 6 4). Cette information déclenche un contact (4) situé à bord de l'aéronef, d'une technologie non limitative selon l'invention, tel que dispositif mécanique ou optoélectronique. Ce dispositif est enclenché par l'effet de la rotation de la tige (2) sur un axe perpendiculaire à l'axe de symétrie de l'aéronef (3). Il peut être enclenché de la même manière par l'information reçue du photorécepteur ou du récepteur ultrasonore. Ce contact, directement relié au calculateur de bord (1) ordonne à l'aéronef de se cabrer 12 selon un angle prédéfini par action sur ses gouvernes, et de maintenir cet angle. Son moteur étant arrêté, l'aéronef poursuit alors son atterrissage à plat sur le ventre jusqu'à son arrêt complet au sol. De même, l'ordre d'enclencher la procédure d'atterrissage peut provenir de la télémétrie optique ou ultra-sonore. Le principe général du dispositif électronique avec le calculateur de bord est représenté sur la figure 6. 236 42 48 1 2906525 A miniaturized calculator (1) embarked on the aircraft takes these four commands in charge on receipt of the single order received from the ground pilot. The aircraft then continues its descent, until the rod (2) touches the ground, or the photoreceptor receives the reflection of the signal emitted by the laser diode (FIG. 5), or else the device Ultrasound receives a signal reflected from the ground at a short distance (Figure 6 4). This information triggers a contact (4) located on board the aircraft, a non-limiting technology according to the invention, such as mechanical or optoelectronic device. This device is engaged by the effect of the rotation of the rod (2) on an axis perpendicular to the axis of symmetry of the aircraft (3). It can be triggered in the same way by the information received from the photoreceptor or the ultrasonic receiver. This contact, directly connected to the on-board computer (1) orders the aircraft to pitch up 12 at a predefined angle per action on its control surfaces, and to maintain this angle. Its engine stopped, the aircraft then continues its landing flat on the belly until its complete stop on the ground. Similarly, the order to start the landing procedure can come from optical telemetry or ultrasonic. The general principle of the electronic device with the on-board computer is shown in FIG.
Claims (7)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0608714A FR2906525A1 (en) | 2006-10-03 | 2006-10-03 | Electronic telemetry device for e.g. minidrone, has controller triggering nose up of non-piloted aircraft along angle predetermined by action on its control surfaces for receiving unique command in all or nothing mode from detecting unit |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0608714A FR2906525A1 (en) | 2006-10-03 | 2006-10-03 | Electronic telemetry device for e.g. minidrone, has controller triggering nose up of non-piloted aircraft along angle predetermined by action on its control surfaces for receiving unique command in all or nothing mode from detecting unit |
Publications (1)
Publication Number | Publication Date |
---|---|
FR2906525A1 true FR2906525A1 (en) | 2008-04-04 |
Family
ID=39185865
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR0608714A Pending FR2906525A1 (en) | 2006-10-03 | 2006-10-03 | Electronic telemetry device for e.g. minidrone, has controller triggering nose up of non-piloted aircraft along angle predetermined by action on its control surfaces for receiving unique command in all or nothing mode from detecting unit |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR2906525A1 (en) |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE531688A (en) * | ||||
US6008742A (en) * | 1997-05-21 | 1999-12-28 | Groves; Duane | Aircraft landing gear warning system |
DE102004029487A1 (en) * | 2004-06-18 | 2006-01-12 | Eads Deutschland Gmbh | Unmanned air craft has missile in bay on top side and has sensor system to turn aircraft through 180 degrees for release |
-
2006
- 2006-10-03 FR FR0608714A patent/FR2906525A1/en active Pending
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE531688A (en) * | ||||
US6008742A (en) * | 1997-05-21 | 1999-12-28 | Groves; Duane | Aircraft landing gear warning system |
DE102004029487A1 (en) * | 2004-06-18 | 2006-01-12 | Eads Deutschland Gmbh | Unmanned air craft has missile in bay on top side and has sensor system to turn aircraft through 180 degrees for release |
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