RO132865A2

RO132865A2 - Aircrafts with vertical take-off and landing

Info

Publication number: RO132865A2
Application number: ROA201700213A
Authority: RO
Inventors: Liviu Grigorian Giurcă
Original assignee: Liviu Grigorian Giurcă
Priority date: 2017-04-10
Filing date: 2017-04-10
Publication date: 2018-10-30

Abstract

The invention relates to an aircraft with vertical take-off and landing, in particular to a hybrid or electric one meant to be used for air transportation of passengers and freight without requiring landing runways. According to the invention, the aircraft has a fuselage (2) and some extendible wings (3) arranged on either side of the fuselage (2) which is provided with a cabin (4), the fuselage (2) having at its rear part an extension in the shape of a frame (5) having two bearing boxes (6), as well as a propulsion system (7) consisting of two multiple thrusters (8) mounted on the fuselage (2), placed in front of the wings (3) and a multiple thruster (9) placed inside the frame (5), mounted on the two bearings (6).

Description

Aeronave cu decolare si aterizare pe verticalaAircraft with take-off and landing on the vertical

Prezenta invenție se refera la aeronave cu decolare si aterizare pe verticala si in special la cele cu acționare hibrida sau electrica utilizate in scopul deplasării pe cale aeriana a oamenilor si mărfurilor fara necesitatea existentei unor piste de aterizare.The present invention relates to aircraft with vertical take-off and landing and in particular to those with hybrid or electric drive used for the purpose of moving people and goods by air without the need for runways.

Aeronavele care au capacitatea de decolare si de aterizare pe verticală combina avantajele elicopterelor, și anume decolarea și aterizarea pe un spațiu limitat sau pe terenuri greu accesibile, cu avantajele avioanelor convenționale, cum ar fi viteza de croazieră crescută și zborul orizontal cel mai eficient energetic. în ultimele decenii, s-au înregistrat progrese semnificative în domeniul avioanelor cu decolare si aterizare pe verticală dar până în prezent un progres economic semnificativ nu a fost atins.Aircraft with the ability to take off and land vertically combine the advantages of helicopters, ie take-off and landing on a limited space or on difficult accessible land, with the advantages of conventional aircraft, such as increased cruise speed and the most energy efficient horizontal flight. In recent decades, significant progress has been made in the field of vertical take-off and landing aircraft, but so far no significant economic progress has been achieved.

Este cunoscuta soluția de aeronava cu decolare si aterizare pe verticala utilizata de Boeing V-22 Osprey care utilizează doua rotoare deschise dispuse la capetele aripilor. Aceasta soluție permite, in afara decolării si aterizării pe verticala, o viteza de croaziera ridicata. Dezavantajul principal al aceastei soluții consta in instabilitatea la decolare in condiții de vint sau rafale deoarece rotoarele fiind acționate de motoare cu turbina nu reacționează cu suficienta rapiditate pentru a compensa oscilațiile aeronavei. Un alt dezavantaj consta in lipsa redundantei sistemului de propulsie, respectiv daca una dintre turbine se defectează aeronava este distrusa instantaneu. Un al treilea dezavantaj major consta in faptul ca in cazul zborului la punct fix, rotoarele nu sunt protejate si orice contact al acestora cu delimitările materiale ale spațiului de zbor conduce la catastrofa.The solution of the vertical take-off and landing aircraft used by the Boeing V-22 Osprey is used, which uses two open rotors arranged at the ends of the wings. This solution allows, besides the take off and landing vertically, a high cruise speed. The main disadvantage of this solution is the instability of take-off in windy or gusty conditions because the rotors being driven by turbine engines do not react quickly enough to compensate for the aircraft's oscillations. Another disadvantage is the lack of redundancy of the propulsion system, ie if one of the turbines is damaged the aircraft is instantly destroyed. A third major disadvantage is that in the case of fixed point flight, the rotors are not protected and any contact of them with the material boundaries of the flight space leads to catastrophe.

O soluție asemantoare este propusa de compania Joby Aviation cu deosebirea ca rotoarele sunt acționate electric. Deși acest sistem prezintă o redundanta ridicata, ramine problema rotoarelor neprotejate ce pot intra in contact cu diverse obiecte sau chiar si cu oameni la aterizare sau decolare.A similar solution is proposed by the company Joby Aviation with the distinction that the rotors are electrically operated. Although this system has a high redundancy, it remains the problem of unprotected rotors that can come into contact with various objects or even with people when landing or taking off.

Ambele soluții descrise anterior prezintă un gabarit important din cauza imposibilității de a plia aripile si a dispunerii rotoarelor ceea ce le face dificil de utilizat in spațiul urban. De asemenea parcarea acestor aeronave in spatii restrinse, ca de exemplu pe o nava, este dificila.Both solutions described above have an important size due to the impossibility of folding the wings and the arrangement of the rotors which makes them difficult to use in the urban space. Also parking these aircraft in confined spaces, such as on a ship, is difficult.

In consecința devine o necesitate realizarea unei aeronave care sa utilizeze un sistem de propulsie foarte sigur in orice condiții, a cărui acționare sa fie foarte simpla si care sa permită plierea aripilor aeronavei.As a consequence, it becomes necessary to create an aircraft that uses a very safe propulsion system under any conditions, whose operation is very simple and which allows the wings of the aircraft to be folded.

Invenția înlătură dezavantajele aratate mai sus prin aceea ca o aeronava cu decolare si aterizare pe verticala utilizează intr-o prima varianta constructiva un sistem modular de propulsie format din trei a 2017 00213The invention eliminates the disadvantages shown above by the fact that an aircraft with vertical take-off and landing uses in a first constructive version a modular propulsion system consisting of three of 2017 00213

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propulsoare multiple, doua situate la partea din fata a aeronavei, respectiv de o parte si de alta a unui fuzelaj, si celalalt situat in poziție mediana la partea din spate a aeronavei. Pentru zborul pe orizontala aeronava folosește niște aripi principale situate de o parte si de alta a fuzelajului. Fiecare aripa principala este formata dintr-o aripa fixa solidara cu fuzelajul si dintr-o aripa mobila care poate fi retrasa in interiorul aripii fixe sau poate fi extinsa atunci cind este scoasa in afara aripii fixe. Fiecare propulsor multiplu conține cel puțin doua rotoare înșirate după o axa principala care coincide sau este paralela cu axa mediana a aeronavei. Fiecare rotor este acționat de un motor electric. Motoarele electrice sunt montate pe un suport comun rotativ iar rotoarele sunt parțial suprapuse unul peste celalalt pentru a micșora spațiul necesar montării si in general volumul total al aeronavei. Propulsoarele multiple se pot roti după o axa perpendiculara pe axa principala, in funcție de regimul de zbor al aeronavei. Propulsoarele multiple anteriore sunt fiecare protejate in timpul decolării si aterizării de un cadru fixat pe de o parte in fuzelaj si pe de alta parte pe aripa corespunzătoare. Propulsorul multiplu aflat la partea din spate este montat in interiorul unui cadru posterior solidar cu fuzelajul aeronavei. La partea din spate aeronava prezintă un ampenaj orizontal fixat prin intermediul a doua profundoare pe cadrul posterior. Ampenajul orizontal este unit cu aripile principale prin intermediul a doi tiranti cu rol de rigidizare.multiple propellers, two located at the front of the aircraft, respectively on one side and the other of a fuselage, and the other located in the median position at the rear of the aircraft. For horizontal flight the aircraft uses some main wings located on either side of the fuselage. Each main wing consists of a fixed wing integral with the fuselage and a movable wing that can be retracted inside the fixed wing or can be extended when removed out of the fixed wing. Each multiple propeller contains at least two rotors connected by a major axis that coincides with or is parallel to the median axis of the aircraft. Each rotor is driven by an electric motor. The electric motors are mounted on a common rotary support and the rotors are partially superimposed on each other to reduce the space required for mounting and in general the total volume of the aircraft. Multiple thrusters can be rotated along a axis perpendicular to the main axis, depending on the flight regime of the aircraft. The multiple front propellers are each protected during take-off and landing by a frame fixed on one side in the fuselage and on the other side on the corresponding wing. The multiple propeller at the rear is mounted inside a rear frame integral with the aircraft's fuselage. At the rear the aircraft has a horizontal tilt fixed by means of two depths on the rear frame. The horizontal coupling is joined to the main wings by means of two tie rods with a stiffening role.

Intr-o a alta varianta constructiva o aeronava cu decolare si aterizare pe verticala utilizează un sistem modular de propulsie format din trei propulsoare multiple, doua situate la partea din fata a aeronavei, respectiv de o parte si de alta a unui fuzelaj, de tipul celor de la exemplul anterior si celalalt posterior situat in poziție mediana la partea din spate a aeronavei. Propulsorul multiplu posterior este de tipul cu ventilatoare inubate si este montat intr-o incinta ce poate fi deschisa in timpul decolarii/aterizari si al zborului de tranziție si este închisa de doua capace pe perioada zborului de croaziera.In another constructive variant, an aircraft with vertical take-off and landing uses a modular propulsion system consisting of three multiple thrusters, two located at the front of the aircraft, respectively on one side and the other of a fuselage, of the type from the previous example and the other posterior located in the median position at the rear of the aircraft. The rear multiple propeller is of the type with fan blades and is mounted in an enclosure that can be opened during takeoff / landing and of the transitional flight and is closed by two caps during the cruise flight.

Invenția prezintă un număr de avantaje importane si anume:The invention presents a number of important advantages, namely:

- Propulsoarele multiple sunt separate de aripile aeronavei iar mecanismul lor de acționare este simplu, fiabil si necesita o putere de antrenare redusa;- The multiple thrusters are separated by the wings of the aircraft and their mechanism of action is simple, reliable and requires a low driving power;

- Rotoarele sun protejate in timpul decolării si aterizării ceea ce micșorează pericolul la contactul cu viteza redusa al delimitărilor materiale ale spațiului de zbor;- The rotors are protected during take-off and landing which reduces the danger of contact with the slow speed of the material delimitations of the flight space;

- La aterizare si decolare prezintă un pericol redus pentru oameni;- At landing and take-off, there is a small danger for people;

- Datorita aripilor retractabile gabaritul aeronavei poate fi redus si aeronava poate fi utilizata in zone urbane, respectiv poate fi parcata in spatii restrinse;- Due to the retractable wings the size of the aircraft can be reduced and the aircraft can be used in urban areas, respectively it can be parked in confined spaces;

- Propulsoarele multiple prezintă o rezistenta redusa la înaintare inclusiv la zborul pe orizontala ceea ce creste viteza maxima si reduce consumul de combustibil;- Multiple thrusters have reduced resistance to advancement including horizontal flight which increases the maximum speed and reduces fuel consumption;

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- Greutatea aeronavei este redusa datorita greutății reduse a sistemelor de acționare ale propulsoarelor multiple;- The weight of the aircraft is reduced due to the reduced weight of the actuators of the multiple propellers;

Se dau mai jos un număr de exemple de realizare a invenției in legătură cu figurile 1, 2, 3, 4, 5, 6, 7, 8, 9,10,11 si 12 care reprezintă:The following are a number of embodiments of the invention in connection with Figures 1, 2, 3, 4, 5, 6, 7, 8, 9,10,11 and 12 which represent:

- Fig. 1, o vedere de sus a unei aeronave cu decolare si aterizare pe verticala de tipul cu trei propulsoare multiple similare si aripi extensibile in poziția de decolare;FIG. 1, a top view of an aircraft with vertical take-off and landing of the type with three similar multiple thrusters and extensible wings in the take-off position;

- Fig. 2, o vedere izometrică a unei aeronave de tipul celei de la figura 1 in poziția de decolare;FIG. 2 is an isometric view of an aircraft of the type shown in figure 1 in the take-off position;

- Fig. 3, o vedere izometrică a unei aeronave de tipul celei de la figura 1, cu propulsoarele multiple in poziția de tranziție;FIG. 3 is an isometric view of an aircraft of the type shown in Figure 1, with multiple thrusters in the transition position;

- Fig. 4, o vedere izometrică a unei aeronave de tipul celei de la figura 1, cu propulsoarele multiple in poziția zborului pe orizontala cu viteza maxima;FIG. 4 is an isometric view of an aircraft of the type shown in Figure 1, with multiple thrusters in the horizontal flight position at maximum speed;

- Fig. 5, o vedere izometrică a unei aeronave de tipul celei de la figura 1, cu propulsoarele multiple anterioare in poziția zborului pe orizontala cu prima viteza de croaziera;FIG. 5 is an isometric view of an aircraft of the type shown in Figure 1, with the multiple front propellers in the horizontal flight position with the first cruise speed;

- Fig. 6, o vedere izometrică a unei aeronave de tipul celei de la figura 1, cu propulsorul multiplu posterior in poziția zborului pe orizontala cu a doua viteza de croaziera;FIG. 6 is an isometric view of an aircraft of the type shown in Figure 1, with the rear multiple propeller in the horizontal flight position with the second cruise speed;

- Fig. 7, o vedere izometrică a unei aeronave cu decolare si aterizare pe verticala de tipul cu trei propulsoare multiple avind aripi fixe si aripi adiționale;FIG. 7, an isometric view of an aircraft with vertical take-off and landing of the type with three multiple thrusters having fixed wings and additional wings;

- Fig. 8, o vedere izometrică a unui propulsor multiplu anterior;FIG. 8 is an isometric view of an anterior multiple propellant;

- Fig. 9, o vedere frontala a propulsorului de la figura 7;FIG. 9 is a front view of the propeller in Figure 7;

- Fig. 10, o vedere izometrică a unei aeronave cu decolare si aterizare pe verticala de tipul cu doua propulsoare multiple cu rotoare deschise situate la partea din fata si cu propulsor multiplu cu ventilatoare intubate la partea din spate, in poziția de decolare;FIG. 10 is an isometric view of an aircraft with vertical take-off and landing of the type with two multiple propellers with open rotors located at the front and with multiple propellers with fans intubated at the rear, in the take-off position;

- Fig. 11, o secțiune verticala prin aeronava de la figura 10 pe perioada zborului de tranziție;FIG. 11, a vertical section through the aircraft of figure 10 during the transitional flight period;

- Fig. 12, o vedere izometrică a unei aeronave de tipul celei de la figura 10, cu propulsoarele multiple in poziția zborului pe orizontala.FIG. 12 is an isometric view of an aircraft of the type shown in Figure 10, with multiple thrusters in the horizontal flight position.

O aeronava 1 cu decolare si aterizare pe verticala prezintă un fuzelaj 2 si niște aripi 3, principale, situate de o parte si de alta a fuzelajului 2, ca in figurile 1, 2, 3, 4, 5 si 6. Fuzelajul 2 prezintă o cabina 4, avind o forma aerodinamica. Fuzelajul 2 se prelungește la partea din spate a aeronavei 1 cu un cadru 5, de forma considerata in general ovala. Cadrul 5 prezintă in zona mediana doua lagare 6. Aeronava 1 utilizează un sistem modular de propulsie 7 format din doua propulsoare multiple 8, susținute de fuzelajul 2, situate in fata aripilor 3, de o parte si de alta a fuzelajului 2, si un propulsor multiplu 9, situat in interiorul cadrului 5, susținut de cele doua lagare 6. Fuzelajul 2 prezintă la partea din spate un plan înclinat superior 10 si un plan înclinat 11 care se intersectează in fata propulsorului a 2017 00213An aircraft 1 with vertical take-off and landing has a fuselage 2 and some main wings 3, located on both sides of the fuselage 2, as in Figures 1, 2, 3, 4, 5 and 6. The fuselage 2 shows a cabin 4, having an aerodynamic shape. The fuselage 2 extends to the rear of the aircraft 1 with a frame 5, generally considered oval in shape. Frame 5 presents in the median area two bearings 6. Aircraft 1 uses a modular propulsion system 7 consisting of two multiple propellers 8, supported by the fuselage 2, located in front of the wings 3, on both sides of the fuselage 2, and a propeller. multiple 9, located inside the frame 5, supported by the two bearings 6. The fuselage 2 shows at the back a superior inclined plane 10 and an inclined plane 11 which intersects in front of the propeller of 2017 00213

10/04/2017 hf multiplu 9 si permit furnizarea de aer necesar propulsiei. Fiecare propulsor multiplu 8 sau 9 conține cel puțin doua rotoare 12 înșirate după o axa principala care coincide sau este paralela cu axa mediana a aeronavei 1. Fiecare rotor 12 este acționat de un motor electric 13. Motoarele electrice 13 sunt montate pe un suport 14, comun, rotativ iar rotoarele 12 sunt parțial suprapuse unul peste celalalt pentru a micșora spațiul necesar montării si in general volumul total al aeronavei 1. Propulsoarele multiple 8 sau 9 se pot roti după o axa perpendiculara pe axa principala, in funcție de regimul de zbor al aeronavei 1. In partea mediana a fiecărui suport 14 este fixat in cazul propulsoarelor multiple anterioare 8 un arbore 15 care poate fi rotit provocind de asemenea rotatia propulsorului multiplu 8. In partea mediana a suportului 14, corespunzător propulsorului multiplu 9 sunt fixați doi arbori 16 care sunt suspendați in lagărele 6 si care pot fi rotiti provocind rotatia propulsorului multiplu 9. Arborii 15 respectiv 16 sunt acționați de niște actuatoare (nefigurate). Propulsoarele multiple 8 anteriore sunt fiecare protejate in timpul decolării si aterizării de un cadru 17 fixat pe de o parte in fuzelajul 2 si pe de alta parte pe aripa 3, corespunzătoare. Fiecare aripa 3 principala este formata dintr-o aripa 18 fixa solidara cu fuzelajul 2 si dintr-o aripa 19 mobila care poate fi retrasa in interiorul aripii 18 fixe sau poate fi extinsa atunci cind este scoasa in afara aripii 18 fixe. La partea din spate aeronava 1 prezintă un ampenaj 20 orizontal fixat prin intermediul a doua profundoare 21 pe cadrul 5 posterior. Ampenajul 20 orizontal este unit cu aripile 3 principale prin intermediul a doi tiranti 22 cu rol de rigidizare. In funcționare, in momentul decolării sau aterizării dintr-un spațiu limitat, aripile 19 mobile ale aripilor 3 sunt retractate in interiorul aripilor 18 fixe in asa fel incit proiecția pe sol a aeronavei 1 sa fie minima (figura 1 si 2). Concomitent propulsoarele multiple 8, respectiv 9 sunt la orizontala in asa fel incit jetul de aer expulzat de ele sa fie îndreptat spre direcția in jos. Cind aeronava 1 se gaseste la o altitudine convenabila, aripile 19 mobile sunt extinse in poziția de funcționare la care portanta oferita de aripile 3 in zborul pe orizontala este maxima. In perioada tranziției de la zborul pe verticala la zborul orizontal propulsoarele multiple 8 respectiv 9 sunt acționate intr-o poziție inclinata ceea ce începe sa imprime o viteza orizontala aeronavei 1 (figura 3). Pe măsură ce viteza orizontala a aeronavei 1 creste datorita componentei orizontale a forței de tracțiune dezvoltata de propulsoarele multiple 8, respectiv 9, sustentatia este preluata parțial de aripile 3, respectiv de ampenajul 20 orizontal. In momentul in care viteza aeronavei 1 a crescut suficient, propulsoarele multiple 8, respectiv 9 ajung in poziție verticala, respectiv jetul expulzat are o traiectorie orizontala si sustentatia este preluata in totalitate de aripile 3, respectiv de ampenajul 20 orizontal 19 (figura 4). Cu propulsoarele multiple 8 si 9 in aceasta poziție aeronava 1 poate obține viteza maxima deoarece componenta de tracțiune pe orizontala este maxima. Daca se dorește ca aeronava 1 sa zboare cu o viteza de croaziera redusa propulsoarele multiple 8 revin in poziție orizontala iar motoarele electrice 13 corespunzătoare sunt oprite (figura 5). In aceasta perioada propulsia pe orizontala este asigurata numai de propulsorul multiplu 9. Daca a 2017 0021310/04/2017 hf multiple 9 and allow the supply of air needed for propulsion. Each multiple propeller 8 or 9 contains at least two rotors 12 drawn along a main axis that coincides with or is parallel to the median axis of the aircraft 1. Each rotor 12 is driven by an electric motor 13. The electric motors 13 are mounted on a support 14, common, rotary and the rotors 12 are partially superimposed on each other to reduce the space required for mounting and in general the total volume of the aircraft 1. Multiple propellers 8 or 9 can rotate along an axis perpendicular to the main axis, depending on the flight regime of the aircraft. of the aircraft 1. In the median part of each support 14 is fixed in the case of the previous multiple propellers 8 a shaft 15 which can also be rotated causing the rotation of the multiple propeller 8. In the median part of the support 14, corresponding to the multiple propeller 9 are fixed two shafts 16 which are suspended in bearings 6 and can be rotated causing the rotation of the multiple propeller 9. The shafts 15 and 16 respectively are acted by some (not shown) actuators. The multiple front propellers 8 are each protected during take-off and landing by a frame 17 fixed on one side in the fuselage 2 and on the other side on the corresponding wing 3. Each main wing 3 is made up of a fixed fixed wing 18 with the fuselage 2 and a movable wing 19 that can be retracted inside the fixed wing 18 or can be extended when removed outside the fixed wing 18. At the rear, the aircraft 1 has a horizontal groove 20 fixed by means of two depths 21 on the rear frame 5. The horizontal engagement 20 is joined to the main wings 3 by means of two straps 22 with a stiffening role. In operation, when taking off or landing from a limited space, the movable wings 19 of the wings 3 are retracted inside the fixed wings 18 so that the projection on the ground of the aircraft 1 is minimal (figures 1 and 2). Simultaneously the multiple propellers 8 and 9 respectively are horizontal so that the jet of air expelled by them is directed in the downward direction. When the aircraft 1 is at a convenient altitude, the movable wings 19 are extended to the operating position at which the lift offered by the wings 3 in the horizontal flight is maximum. During the transition from vertical to horizontal flight, the multiple propellers 8 and 9 respectively are actuated in an inclined position which begins to print a horizontal speed of aircraft 1 (figure 3). As the horizontal speed of the aircraft 1 increases due to the horizontal component of the traction force developed by the multiple propellers 8, respectively 9, the support is partially taken over by the wings 3, respectively by the horizontal gear 20. When the speed of the aircraft 1 has increased sufficiently, the multiple thrusters 8, respectively 9 reach the vertical position, respectively the expelled jet has a horizontal trajectory and the support is taken entirely by the wings 3, respectively by the horizontal gear 20 (figure 4). With multiple thrusters 8 and 9 in this position aircraft 1 can achieve maximum speed because the horizontal traction component is maximum. If it is desired that the aircraft 1 fly at a low cruise speed the multiple thrusters 8 return to the horizontal position and the corresponding electric motors 13 are stopped (Figure 5). In this period the horizontal propulsion is provided only by the multiple propeller 9. If 2017 00213

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se dorește ca aeronava 1 sa zboare cu o viteza de croaziera ridicata propulsorul multiplu revine in poziție orizontala iar motoarele electrice 13 corespunzătoare sunt oprite (figura 6). In aceasta perioada propulsia pe orizontala este asigurata numai de propulsoarele multiple 9. La aterizare procesul se inversează. Controlul aeronavei 1 este asigurat prin schimbarea unghiului de înclinare al propulsoarelor multiple 8 in comparație cu unghiul de înclinare al propulsorului multiplu 9, respectiv prin variația turației motoarelor electrice ce actioneaza rotoarele 12. In cazul defectării unui motor 13, celalalt motor 13, ramas funcțional din cele doua de pe fiecare propulsor, este accelerat la o turatie care poate compensa defectul.it is desired that the aircraft 1 fly at a high cruise speed the multiple propeller returns to the horizontal position and the corresponding electric motors 13 are stopped (figure 6). During this period, horizontal propulsion is provided only by multiple propellers 9. At landing, the process is reversed. The control of the aircraft 1 is ensured by changing the inclination angle of the multiple propellers 8 in comparison with the inclination angle of the multiple propellers 9, respectively by the variation of the speed of the electric motors operating the rotors 12. In case of failure of one engine 13, the other engine 13, remained functional from the two on each propeller, is accelerated to a speed that can compensate for the defect.

Intr-o alta varianta o aeronava 40 are in principal aceiași configurație ca cea din exemplul anterior avid niște aripi 41, fixe unite cu ampenajul 20 orizontal prin intermediul tirantilor 22, ca in figura 7. In aceasta configurație aeronava 40 este utilizata pentru zborul pe distante scurte sau in oraș. In cazul zborului de lunga durata aeronavei 40 i se pot atașa doua aripi 42 adiționale prin intermediul unor cepi 43. Fiecare cep 43 intra intr-o cupla rapida 44 fixata in interiorul aripii 41. In funcționare cu ajutorul aripilor 42 adiționale autonomia aeronavei 40 creste foarte mult.In another embodiment, an aircraft 40 has mainly the same configuration as that of the previous example, avid wings 41, fixed joined to the horizontal 20 by means of tie rods 22, as in figure 7. In this configuration the aircraft 40 is used for the distance flight. short or in the city. In the case of the long-haul flight of the aircraft 40, two additional wings 42 can be attached by means of staves 43. Each strap 43 enters a fast coupling 44 fixed inside the wing 41. In operation with the help of the additional wings 42 the autonomy of the aircraft 40 greatly increases a lot.

Intr-o alta varianta constructiva un propulsor multiplu 60 conține un număr de rotoare 12 acționate de motoarele electrice 13 ca in figurile 8 si 9. Motoarele electrice 13 sunt unite prin intermediul a doua brațe 61 ce se pot roti cu un unghi l\ZI intr-un lagar 62 acționate de un actuator (nefigurat). Lagarul 62 este fixat rigid de arborele 15. Odata cu rotatia motoarelor electrice 13 se rotesc si rotoarele 12, ceea ce imbunatateste controlul aeronavei la viteze scăzute si eventual atunci cind exista vint lateral.In another embodiment, a multiple propeller 60 contains a number of rotors 12 actuated by the electric motors 13 as in Figures 8 and 9. The electric motors 13 are connected by means of two arms 61 which can rotate with an angle l \ ZI in. - a bearing 62 actuated by an actuator (not shown). The bearing 62 is rigidly fixed by the shaft 15. With the rotation of the electric motors 13 the rotors 12 also rotate, which improves the control of the aircraft at low speeds and possibly when there is lateral wind.

Intr-o alta varianta o aeronava 80 cu decolare si aterizare pe verticala prezintă un fuzelaj 81 de forma considerata in general cilindrica ca in figurile 10,11 si 12. Aeronava 80 folosește un sistem modular de propulsie 82 care utilizeza doua propulsoare multiple 83, situate la partea din fata a aeronavei 80, respectiv de o parte si de alta a fuzelajului 81. Propulsoare multiple 83 sunt de tipul celor de la exemplul anterior. Sistem modular de propulsie 82 conține de asemenea un propulsor multiplu 84, posterior, montat intr-o incinta 85 aflata in poziție mediana la partea din spate a aeronavei 80. Propulsorul multiplu 84 posterior este de tipul cu ventilatoare inubate si este sprijini in partea mediana pe doi arbori (nefigurati) ce pot fi rotiti de un actuator (nefigurat). Incinta 85 poate fi deschisa in timpul decolarii/aterizari si al zborului de tranziție si este închisa de un capac 86 superior si de un capac 87, inferior pe perioada zborului de croaziera. In funcționare, propulsoarele multiple 83, respectiv 84 sunt la orizontala in asa fel incit jetul de aer expulzat de ele sa fie îndreptat spre direcția in jos (figura 10). In perioada tranziției de la zborul pe verticala la zborul orizontal propulsoarele multiple 83 respectiv 84 sunt acționate intr-o poziție inclinata ceea ce începe sa a 2017 00213In another embodiment, an aircraft 80 with vertical take-off and landing has a fuselage 81 of generally considered cylindrical shape as in Figures 10, 11 and 12. The aircraft 80 uses a modular propulsion system 82 using two multiple propellers 83, located at the front of the aircraft 80, respectively on both sides of the fuselage 81. Multiple propellers 83 are of the type of those in the previous example. Modular propulsion system 82 also contains a multiple propeller 84, rear mounted in an enclosure 85 located in the median position at the rear of the aircraft 80. The multiple propeller 84 rear is of the type with bladed fans and is supported in the median part on two shafts (not shown) that can be rotated by an actuator (not shown). The enclosure 85 can be opened during take-off / landing and of the transitional flight and is closed by an upper cover 86 and a lower cover 87, during the cruise flight period. In operation, the multiple thrusters 83 and 84 respectively are horizontal so that the jet of air expelled by them is directed in the downward direction (figure 10). During the transition from vertical to horizontal flight, multiple thrusters 83 and 84 respectively are actuated in an inclined position which starts in 2017 00213

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imprime o viteza orizontala aeronavei 80 (figura 11). Pe măsură ce viteza orizontala a aeronavei 80 creste datorita componentei orizontale a forței de tracțiune dezvoltata de propulsoarele multiple 83, respectiv 84, sustentatia este preluata parțial de aripile 3, respectiv de ampenajul 20 orizontal. In momentul in care viteza aeronavei 80 a crescut suficient, propulsoarele multiple 83 ajung in poziție verticala, respectiv jetul expulzat are o traiectorie orizontala si sustentatia este preluata in totalitate de aripile 3, respectiv de ampenajul 20 orizontal (figura 12). Concomitent propulsorul multiplu 84 este adus in poziție orizontala si incinta 85 este închisa de capacele 86, respectiv 87.prints a horizontal speed of aircraft 80 (Figure 11). As the horizontal speed of the aircraft 80 increases due to the horizontal component of the traction force developed by the multiple thrusters 83, respectively 84, the support is partially taken over by the wings 3, respectively by the horizontal gear 20. When the speed of the aircraft 80 has increased sufficiently, the multiple thrusters 83 reach the vertical position, respectively the expelled jet has a horizontal trajectory and the support is taken entirely by the wings 3, respectively by the horizontal gear 20 (figure 12). At the same time, the multiple propeller 84 is brought to a horizontal position and the enclosure 85 is closed by the covers 86 and 87 respectively.

Aeronavele 1, 40, respectiv 80 pot avea dimensiuni foarte mici, si in acest caz sunt utilizate ca drone, pot avea dimensiuni medii, si in acest caz sunt utilizate pentru transportul de persoane sau mărfuri sau pot avea dimensiuni foarte mari, si in aces caz pot fi utilizate pentru a ridica greutati foarte mari sau in alte scopuri diverse.Aircraft 1, 40 and 80 respectively can have very small dimensions, and in this case they are used as drones, they can have medium size, and in this case they are used for the transport of people or goods or they can have very large dimensions, and in that case they can be used to lift very heavy weights or for various other purposes.

Sistemele modulare de propulsie descrise pot sa folosească o unitate de putere hibrida, sau una pur electrica.The modular propulsion systems described may use a hybrid power unit, or a pure electric one.

Oricare combinații posibile ale soluțiilor descrise anterior pot fi considerate ca facind parte din descriere si revendicări.Any possible combinations of the solutions described above can be considered as part of the description and claims.

Claims

claims

1. Vertical take-off and landing aircraft, characterized in that an aircraft (1) uses a modular propulsion system (7) consisting of three multiple thrusters and the multiple thrusters are protected against contact with the material boundaries of the surrounding space during takeoff, landing. or fixed-point flight, when necessary, respectively when accidental contact with the iconic space is possible without causing accidents, and multiple thrusters are unprotected in the case of transient and horizontal flight, respectively when not required.

The aircraft as claimed in claim 1, characterized in that two multiple thrusters (8) are placed at the front of the aircraft (1) and a multiple thruster (9) is placed at the rear of the aircraft (1) and the multiple thrusters ( 8) are supported by a fuselage (2) of the aircraft (1), being mounted on both sides of the fuselage (2), and the multiple propeller (9) is mounted inside a frame (5), supported by two bearings (6), and each multiple propeller (8) or (9) contains at least two open type rotors (12), drawn along a main axis which coincides with or is parallel to the median axis of the aircraft (1), and each rotor (12) is driven by an electric motor (13), and two electric motors (13) are mounted on a support (14), common, rotary and the corresponding two rotors (12) are partially superimposed on each other to reduce the space necessary for mounting and in general the total volume of the aircraft (1).

3. The aircraft as in claim 2, characterized in that the multiple thrusters (8) or (9) can rotate along a axis perpendicular to the main axis, depending on the flight regime of the aircraft (1), and in the case of the previous multiple thrusters ( 8) in the median part of each support (14) is fixed a shaft (15) which can also be rotated causing the rotation of the multiple propeller (8), and in the case of the multiple propeller (9) in the median part of the support (14) are fixed two shafts (16) which are suspended in the bearings (6) and which can be rotated causing the rotation of the multiple propeller (9), and the shafts (15) respectively (16) are actuated by some actuators.

The aircraft as claimed in claim 3, characterized in that the fuselage (2) has two wings (3) located on one side and the other of the fuselage (2), and

Behind the cabin (4) the aircraft (1) has a superior inclined plane (10) and an inclined plane (11) that intersect in front of the multiple propeller (9) and allow the supply of air needed for the propulsion, and 2017 00213

10/04/2017 The frame (5) is built to extend the fuselage (2), and the multiple propellers (8) are mounted in front of the wings (3), and the multiple front propellers (8) are each protected during takeoff, landing and landing. the flight at a fixed point by a frame (17) fixed on one side in the fuselage (2) and on the other side on the wing (3), corresponding.

5. The aircraft as claimed in claim 4, characterized in that each main wing (3) is formed by a fixed wing (18) integral with the fuselage (2) and a movable wing (19) which can be retracted inside the wing ( 18) fixed or can be extended when it is removed out of the wing (18) fixed, and at the rear of the aircraft (1) has a horizontal fence (20) fixed by means of two depths (21) on the rear (5) , and the horizontal gear (20) is joined to the main wings (3) by means of two straps (22) with a stiffening role.

6. The aircraft as in claim 5, characterized in that in operation, when taking off or landing from a limited space, the movable wings (19) of the wings (3) are retracted inside the wings (18) fixed so that the projection on the ground of the aircraft (1) should be minimal, and at the same time the multiple thrusters (8) and (9) are horizontal so that the jet of air expelled by them is directed in the downward direction, and when the aircraft (1) is find at a suitable altitude, the movable wings (19) are extended to the operating position at which the load offered by the wings (3) in the horizontal flight is maximum, and during the transition from the vertical flight to the horizontal flight the multiple propellers (8) respectively (9) are actuated in an inclined position which begins to print a horizontal speed of the aircraft (1), and as the horizontal speed of the aircraft (1) increases due to the horizontal component of the tensile force develops your of the multiple propellers (8), respectively (9), the support is partially taken by the wings (3), respectively by the horizontal gear (20), and when the speed of the aircraft (1) has increased sufficiently, the multiple propellers (8) , respectively (9) reach the vertical position, respectively the expelled jet has a horizontal trajectory and the support is taken entirely by the wings (3), respectively by the horizontal gear (20) (19) and with the multiple thrusters (8) and (9) in this position the aircraft (1) can achieve maximum speed because the horizontal traction component is maximum.

7. The aircraft as in claim 6 characterized in that for a low cruise speed of the aircraft (1), the multiple thrusters (8) return to the horizontal position and the corresponding electric motors (13) are stopped and the horizontal propulsion is provided only by the propeller. multiple (9).

to 2017 00213

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8. The aircraft as in claim 6, characterized in that for a high cruise speed of the aircraft (1) the multiple propeller (

9) returns to the horizontal position, the corresponding electric motors (13) being stopped and in this period the horizontal propulsion is provided only by the multiple thrusters (9).

10. The aircraft as in claim 6 characterized in that at the landing of the aircraft (1) the process is reversed.

11. The aircraft as in claim 6, characterized in that the control of the aircraft (1) is ensured by changing the inclination angle of the multiple propellers (8) compared to the inclination angle of the multiple propeller (9), respectively by the variation of the speed of the electric motors operating. The rotors (12), and in case of failure of one engine (13), the other engine (13), remaining functional of the two on each multiple propeller (8) or (9), is accelerated at a speed that can compensate for the defect.

12. The aircraft as claimed in claim 4, characterized in that an aircraft (40) has wings (41), fixed fixed with the hinge (20) horizontally through tyrannies (22), and the wings (41) can be extended with some wings ( 42) additional, and each wing (42), the additional has some strains (43), and each wing (41), the fixed one has some fast couplings (44), and each wing (42), the additional can be attached to the wing (41) , suitable fixed by means of the screws (43) and the quick couplings (44) which can be combined to ensure the rigid attachment of the wing (42), additional wing (41), fixed.

13. The aircraft as in claim 12, characterized in that the aircraft (40) has different configurations depending on the mission accomplished.

14. The aircraft as in claim 13, characterized in that the aircraft (40) has a simple configuration, without additional wings (42) in the case of urban missions, respectively of short duration.

15. The aircraft as in claim 13, characterized in that the aircraft (40) has a configuration in which additional wings (42) are attached to the aircraft (40) in the case of long-term missions, respectively over long distances.

16. Multiple propeller characterized by the fact that the multiple propeller (60) contains a number of rotors (12) driven by the electric motors (13), the electric motors (13) being joined by means of two arms (61) which can be rotated by a angle M in a bearing (62) operated by an actuator, of 2017 00213

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7 | and the bearing (62) is rigidly fixed to the shaft (15).

17. Propeller as in the revication 16 characterized by the fact that in operation with the rotation of electric motors (13) and rotors (12), which improves control of the aircraft at low speeds and possibly when there is lateral wind.

18. The aircraft as claimed in claim 3, characterized in that an aircraft (80) with vertical take-off and landing has a fuselage (81), of generally considered cylindrical shape, and the aircraft (80) uses a modular propulsion system (82). which uses two multiple propellers (83), located at the front of the aircraft (80), respectively on one side and the other of the fuselage (81) and a multiple propeller (84), rear mounted in an enclosure (85) located in the middle position at the rear of the aircraft (80), and the multiple propeller (84) rear is of the type with fan blades and is supported in the middle on two shafts that can be rotated by an actuator, and the enclosure (85) can be opened during take-off / landing and of the transitional flight and is closed by an upper cover (86) and a cover (87), lower during the cruise flight period.

19. The aircraft as in claim 18 characterized in that In operation, the multiple thrusters (83) and respectively (84) are horizontal so that the air jet ejected by them is directed in the downward direction, and during the transition period. in the vertical flight in the horizontal flight the multiple thrusters (83) respectively (84) are actuated in an inclined position which begins to print a horizontal speed of the aircraft (80) and as the horizontal speed of the aircraft (80) increases due to the horizontal component of the tensile force developed by the multiple thrusters (83) and (84) respectively, the support is partially taken by the wings (3), respectively by the horizontal gear (20), and when the speed of the aircraft (80) has increased sufficiently, the thrusters multiple (83) reach the vertical position, respectively the ejected jet has a horizontal trajectory and the support is taken entirely by the wings (3), respectively by the horizontal impingement (20) and concom the multiple thruster (84) is brought to the horizontal position and the enclosure (85) is closed by the covers (86) and (87) respectively.

20. The aircraft as in claims 3,12 and 18, characterized in that the energy required to operate the multiple thrusters is obtained from a set of electric batteries.

21. The aircraft as claimed in claims 3,12 and 18, characterized in that the energy required to operate the multiple thrusters is obtained from a hybrid system.