RO137338A2

RO137338A2 - INDIVIDUAL AIRCRAFT WITH VERTICAL TAKEOFF AND LANDING-VTOL

Info

Publication number: RO137338A2
Application number: ROA202100579A
Authority: RO
Inventors: Liviu Grigorian Giurcă; Dan Ion Oprea
Original assignee: Liviu Grigorian Giurcă; Dan Ion Oprea
Priority date: 2021-09-27
Filing date: 2021-09-27
Publication date: 2023-03-30

Abstract

The invention relates to an individual aircraft with vertical takeoff and landing, having a distributed electric propulsion system, to be used for a person's travel by air. According to the invention, the aircraft has six front, middle and rear rotors (2, 3 and 4), which are symmetrically attached onto an energy block (5), each of the six front, middle and rear rotors (2, 3 and 4) being driven by a front, middle and rear motor (6, 7 and 8), each middle motor (7) being fixed onto the energy block (5) by means of a main arm (9), on each main arm (9) there being fixed two front and rear arms (10 and 11), which support the front and rear motors (6 and 7) and the corresponding front and rear rotors (2 and 4), respectively, a frame (13) that supports a pilot (14) being fixed onto the energy block (5) by means of a vertical pillar (12).

Description

___________RO 137338 A2___________RO 137338 A2

OFICIUL DE STAT PENTRU INVENȚII Șl MApC; Cerere brevet de invențieSTATE OFFICE FOR INVENTIONS Etc MApC; Patent application

Nr. Data denozitNo. Denied date

Aeronava individuala cu decolare si aterizare pe verticala - VTOLIndividual aircraft with vertical takeoff and landing - VTOL

Prezenta invenție se refera la o aeronava individuala cu decolare si aterizare pe verticala - VTOL, avind un sistem de propulsie electrica distribuita, utilizabila in scopul deplasării pe cale aeriana a unei persoane.The present invention refers to an individual aircraft with vertical take-off and landing - VTOL, having a distributed electric propulsion system, usable for the purpose of moving a person by air.

Sunt cunoscute soluțiile de aeronave cu decolare si aterizare pe verticala la care fuzelajul este poziționat pe verticala in timpul decolării si aterizării si este poziționat orizontal pe perioada zborului pe orizontala. O astfel de aeronava poate adăposti un singur pilot ca la soluția NASA Puffin. In zborul orizontal pilotul se gaseste intr-o poziție incomoda in care vizibilitatea exterioara este puternic afectata.Aircraft solutions with vertical take-off and landing are known, where the fuselage is positioned vertically during take-off and landing and is positioned horizontally during horizontal flight. Such an aircraft can accommodate a single pilot as in NASA's Puffin solution. In horizontal flight, the pilot finds himself in an uncomfortable position in which external visibility is strongly affected.

O mare parte a soluțiilor de aeronave VTOL utilizează sisteme de propulsie separate pentru zborul pe orizontala si pentru zborul pe verticala ceea ce complica construcția, creste greutatea aeronavei si prezintă un cost ridicat. Pe de alta parte majoritatea acestor sisteme utilizează aripi pivotate sau elici pivotante. Toate aceste sisteme de propulsie direcționale sunt acționate de mecanisme complicate si scumpe.A large part of VTOL aircraft solutions use separate propulsion systems for horizontal flight and for vertical flight, which complicates the construction, increases the weight of the aircraft and presents a high cost. On the other hand, most of these systems use pivoting wings or pivoting propellers. All these directional propulsion systems are operated by complicated and expensive mechanisms.

Este cunoscuta o soluție comerciala propusa in invenția EP1855941 de către Martin Aircraft Company Limited pentru o aeronava individuala. Aceasta soluție utilizeza doua ventilatoare intubate paralele dispuse pe verticala acționate de un singur motor cu ardere interna prin intermediul unor curele. Un dezavantaj al acestei soluții este redundanta foarte redusa. In aces caz, defectarea unei singure piese din lanțul cinematic poate conduce la o catastrofa.A commercial solution proposed in the invention EP1855941 by Martin Aircraft Company Limited for an individual aircraft is known. This solution uses two vertically arranged parallel intubated fans driven by a single internal combustion engine by means of belts. A disadvantage of this solution is the very low redundancy. In this case, the failure of a single part of the kinematic chain can lead to a catastrophe.

Este de asemenea cunoscuta o soluție de aeronava VTOL individuala cu doua rotoare. Aceasta soluție prezintă un nivel de redundanta redus si in cazul defectului unuia dintre rotoare poate avea loc un accident grav. Același lucru se poate intimpla si la soluțiile cu trei sau patru rotoare.A single VTOL aircraft solution with two rotors is also known. This solution has a low level of redundancy and in the event of the failure of one of the rotors, a serious accident may occur. The same thing can happen to solutions with three or four rotors.

Majoritatea soluțiilor de aeronave VTOL individuale sunt foarte complicate si in consecința foarte costisitoare.Most individual VTOL aircraft solutions are very complicated and consequently very expensive.

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 o eficienta ridicata atit in zborul pe verticala cit si in zborul pe orizontala. De asemenea reprezintă o necesitate realizarea unui vehicul aerian cu un preț redus de achiziție si de întreținere.As a consequence, it becomes a necessity to create an aircraft that uses a very safe propulsion system in any conditions, the operation of which is very simple and which allows a high efficiency both in vertical flight and in horizontal flight. It is also a necessity to create an air vehicle with a low purchase and maintenance price.

Invenția înlătură dezavantajele aratate mai sus prin aceea ca o aeronava individuala utilizează sase rotoare deschise, fiecare fiind acționat de un motor electric. Motoarele electrice sunt suspendate simetric prin intermediul unor brațe de un bloc energetic, deasupra centrului de greutate al aeronavei. Pe blocul energetic este fixat un cadru cu o structura foarte simpla ce susține de asemenea un pilot si un tren de aterizare. Blocul energetic conține niște baterii electrice, un sistem de control al acestora, un sistem de control al turației motoarelor electrice si doua joystickuri amplasate simetric pe partlie laterale. Rotoarele deschise se suprapun pe anumite porțiuni ceea ce reduce dimensiunile exterioare. Controlul aeronavei este realizat prin variația turatie diverselor motoare electrice in mod diferit sau altfel spus, prin diferențierea tracțiunii dezvoltate de rotoare.The invention removes the disadvantages shown above in that an individual aircraft uses six open rotors, each driven by an electric motor. The electric motors are suspended symmetrically by means of arms from an energy block, above the center of gravity of the aircraft. A frame with a very simple structure is fixed on the energy block which also supports a pilot and a landing gear. The energy block contains some electric batteries, a control system for them, a control system for the speed of the electric motors and two joysticks placed symmetrically on the side parts. The open rotors overlap on certain portions which reduces the outer dimensions. The control of the aircraft is achieved by varying the speed of the various electric motors in a different way, or in other words, by differentiating the traction developed by the rotors.

Intr-o alta varianta de realizare blocul energetic conține un număr de baterii portabile clipsabile ce pot fi înlocuite rapid atunci cind sunt descărcate, aeronava fiind imediat pregatitata pentru următorul zbor.In another embodiment, the energy block contains a number of clip-on portable batteries that can be quickly replaced when they are discharged, the aircraft being immediately prepared for the next flight.

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

Greutatea aeronavei este redusa datorita utilizării unui număr redus de componente;The weight of the aircraft is reduced due to the use of a reduced number of components;

Sistemul cu rotoare multiple este redundant si in cazul defectării unuia sau a doua motoare electrice aeronava continua sa funcționeze in siguranța;The system with multiple rotors is redundant and in case of failure of one or two electric motors, the aircraft continues to operate safely;

Aeronava individuala prezintă o dimensiune extrem de compacta ceea ce o face sa fie bine adaptata utilizării urbane;The individual aircraft has an extremely compact size, which makes it well adapted to urban use;

Aeronava individuala, avind o construcție simpla, prezintă un cost redus de utilizare si de întreținere;The individual aircraft, having a simple construction, presents a low cost of use and maintenance;

Coeficientul de utilizare al aeronavei este ridicat deoarece bateriile se pot înlocui foarte rapid.The utilization coefficient of the aircraft is high because the batteries can be replaced very quickly.

Se dau mai jos un număr de exemple de realizare a modelului de utilitate în legătură cu figurile 1, 2, 3, 4, 5, 6, 7,8, 9,10 si 11 care reprezintă:Below are a number of examples of the realization of the utility model in relation to figures 1, 2, 3, 4, 5, 6, 7,8, 9,10 and 11 which represent:

Fig. 1, o vedere izometrica dinspre fata a unei aeronave individuale de tipul cu sase rotoare deschise si pilotul stind in picioare, in poziția decolării sau aterizări;Fig. 1, an isometric front view of an individual aircraft of the open six-rotor type with the pilot standing, in the take-off or landing position;

Fig. 2, o vedere laterala cu secțiune a aeronavei de la figura 1;Fig. 2, a side sectional view of the aircraft of Figure 1;

Fig. 3, o vedere de sus a aeronavei de la figura 1;Fig. 3, a top view of the aircraft of figure 1;

Fig. 4, o vedere izometrica dinspre fata a aeronavei de la figura 1 in poziția de zbor orizontal;Fig. 4, an isometric view from the front of the aircraft from figure 1 in the horizontal flight position;

Fig. 5, o vedere izometrica dinspre fata a unei aeronave individuale de tipul cu sase rotoare deschise cu pilotul stind in picioare, avind cadru ranforsat;Fig. 5, a front isometric view of an individual aircraft of the open six-rotor type with the pilot standing, having a reinforced frame;

Fig. 6, un detaliu al unui bloc energetic cu baterii portabile clipsabile;Fig. 6, a detail of a clip-on portable battery power pack;

Fig. 7, detaliu de montaj al unei baterii portabile clipsabile;Fig. 7, assembly detail of a clip-on portable battery;

Fig. 8, o vedere izometrica dinspre fata a unei aeronave individuale de tipul cu sase rotoare deschise si pilotul stind pe scaun, in poziția decolării sau aterizări;Fig. 8, a front isometric view of an individual aircraft of the open six-rotor type with the pilot sitting in the seat, in the take-off or landing position;

Fig. 9, o vedere laterala a aeronavei de la figura 8;Fig. 9, a side view of the aircraft of figure 8;

Fig. 10, o vedere izometrica dinspre fata a aeronavei de la figura 8 in poziția de zbor orizontal;Fig. 10, an isometric view from the front of the aircraft of figure 8 in the horizontal flight position;

Fig. 11, o vedere laterala a aeronavei de la figura 8 avind rotoare protejate.Fig. 11, a side view of the aircraft of Figure 8 having rotors protected.

Intr-o prima varianta constructiva o aeronava 1, individuala, cu decolare si aterizare pe verticala, utilizează sase rotoare, din care doua anterioare 2, doua mediane 3 si doua posterioare 4, care sunt atașate simetric pe un bloc energetic 5, ca in figura 1, 2, 3 si 4. Fiecare rotor anterior 2 este antrenat de un motor anterior 6. Fiecare rotor median 3 este antrenat de un motor median 7. Fiecare rotor posterior 4 este antrenat de un motor posterior 8. Blocul energetic 5, ce se constituie ca o piesa foarte rigida si robusta, conține niște baterii electrice, un sistem de control al acestora si un sistem de control al turației motoarelor electrice (nefigurate) ce servesc alimentarii cu energie a aeronavei 1. Fiecare motor median 7 este fixat pe blocul energetic 5 prin intermediul unui braț principal 9. Pe fiecare braț principal 9 este fixat un braț anterior 10 si un braț posterior 11. Fiecare braț anterior 10 susține motorul anterior 6, respectiv rotorul anterior 2, corespunzător. Fiecare braț posterior 11 susține motorul posterior 8, respectiv rotorul posterior 4, corespunzător. Planul de rotatie al rotrului median 3 este situat sub planul de rotatie al rotorului anterior 2 si al rotorului posterior 4. Planul de rotatie al rotorului anterior 2 si cel al rotorului posterior 4 este suprapus pe o anumita porțiune peste planul de rotatie al rotorului median 3. Pe blocul energetic 5 este fixat prin intermediul unui stilp vertical 12 un cadru 13, care susține un pilot 14. Pilotul 14 sta in poziția in picioare sprijinit pe un suport 15. Dedesubtul suportului 15 este fixat un tren de aterizare 16. Trenul de aterizare 16 este preferabil construit din doua bare 17, curbate spre in jos si care sunt încrucișate. Pe brațele principale 9, respectiv de o parte si de alta a pilotului 14 sunt fixate simetric doua scuturi de protecție 18 care au rolul de a proteja pilotul 14 in cazul dezintegrării unor rotoare anterioare 2, mediane 3 si posterioare 4. Pe partlie laterale ale blocului energetic 5 sunt atașate simetric doua joystickuri 15 utilizate pentru manevrarea aeronavei 1. In caz de defect total pilotul 14 poate folosi o parașuta ejectabila 19, atașata pe spate ca in figura 2. Pe lingă funcția principala de alimentare cu energie, blocul energetic 5 se constituie ca o piesa centrala pe care se fixeaza direct sau indirect toate elementele componente ale aeronavei 1. Toate componentele aeronavei 1 sunt astfel amplasate incit centrul ei de greutate sa fie situat sub centrul de presiune, acest lucru asigurind stabilitatea aeronavei 1 inclusiv in condiții de vint lateral. Controlul aeronavei 1 este realizat prin variația turatie diverselor motoare 6, 7 si 8 in mod diferit sau altfel spus, prin diferențierea tracțiunii dezvoltate de rotoarele anterioare 2, mediane 3 si posterioare 4. La decolare/aterizare toate rotoarele anterioare 2, mediane 3 si posterioare 4 sunt acționate simultan la aceiași turatie. In tranziție si in zbor orizontal rotoarele posterioare 4 sunt accelerate suplimentar si aeronava 1 se înclina spre in fata ca in figura 4. In cazul virajului spre stingă, rotorul median 3 din partea dreapta este accelerat suplimentar. In cazul virajului spre dreapta, rotorul median 3 din partea stingă este accelerat suplimentar.In a first constructive variant, an individual aircraft 1, with vertical take-off and landing, uses six rotors, of which two front 2, two median 3 and two rear 4, which are symmetrically attached to an energy block 5, as in the figure 1, 2, 3 and 4. Each front rotor 2 is driven by a front motor 6. Each middle rotor 3 is driven by a middle motor 7. Each rear rotor 4 is driven by a rear motor 8. The energy block 5, which it is like a very rigid and robust part, it contains some electric batteries, a control system for them and a control system for the speed of the electric motors (not shown) that serve to supply energy to the aircraft 1. Each median motor 7 is fixed on the energy block 5 by means of a main arm 9. A front arm 10 and a rear arm 11 are fixed on each main arm 9. Each front arm 10 supports the front motor 6, respectively the front rotor 2, respectively. Each rear arm 11 supports the rear motor 8, respectively the rear rotor 4, respectively. The plane of rotation of the middle rotor 3 is located below the plane of rotation of the front rotor 2 and of the rear rotor 4. The plane of rotation of the front rotor 2 and that of the rear rotor 4 is overlapped on a certain portion over the plane of rotation of the middle rotor 3 On the energy block 5, a frame 13 is fixed by means of a vertical pillar 12, which supports a pilot 14. The pilot 14 stands in a standing position supported on a support 15. A landing gear 16 is fixed below the support 15. The landing gear 16 is preferably constructed from two bars 17, curved downwards and which are crossed. On the main arms 9, respectively on one side and on the other of the pilot 14, two protective shields 18 are fixed symmetrically, which have the role of protecting the pilot 14 in case of disintegration of the front 2, middle 3 and rear rotors 4. On the side parts of the block two joysticks 15 used to maneuver the aircraft 1 are symmetrically attached to the energy unit 1. In case of total failure, the pilot 14 can use an ejectable parachute 19, attached to the back as in figure 2. Besides the main function of energy supply, the energy block 5 is as a central part on which all the components of the aircraft 1 are fixed directly or indirectly. All the components of the aircraft 1 are placed in such a way that its center of gravity is located below the center of pressure, this ensuring the stability of the aircraft 1 including in side wind conditions . The control of the aircraft 1 is achieved by varying the speed of the various engines 6, 7 and 8 in a different way or, in other words, by differentiating the traction developed by the front 2, middle 3 and rear 4 rotors. During take-off/landing all the front 2, middle 3 and rear rotors 4 are operated simultaneously at the same speed. In transition and in horizontal flight, the rear rotors 4 are additionally accelerated and the aircraft 1 leans forward as in figure 4. In the case of the left turn, the middle rotor 3 on the right side is additionally accelerated. In the case of turning to the right, the middle rotor 3 on the left side is additionally accelerated.

Intr-o alta varianta constructiva derivata din cea anteriora o aeronava 30 utilizează doi stilpi verticali 31, incluși intr-un cadru 32 si care fac legătură intre blocul energetic 5 si suportul 15, ca in figura 5. Pilotul 14 sta in poziția in picioare sprijinit pe suportul 15.In another constructive variant derived from the previous one, an aircraft 30 uses two vertical pillars 31, included in a frame 32 and which connect the energy block 5 and the support 15, as in figure 5. The pilot 14 stands in a standing position supported on support 15.

Intr-o alta varianta constructiva derivata din cele anterioare un bloc energetic 40 conține un număr de baterii 41, portabile si clipsabile, ca in figurile 6 si 7. Bateriile 41 pot fi înlocuite rapid atunci cind sunt descărcate, aeronava 1 fiind imediat pregătită pentru următorul zbor. Fiecare baterie 41 poate fi basculata pe un ax 42 fiind actionata de la un miner 43, ca in figura 6. Minerul 43 servește si la trasportul bateriei 41.In another constructive variant derived from the previous ones, an energy block 40 contains a number of portable and clip-on batteries 41, as in figures 6 and 7. The batteries 41 can be quickly replaced when they are discharged, the aircraft 1 being immediately ready for the next flight. Each battery 41 can be tipped on a shaft 42 being actuated by a miner 43, as in figure 6. The miner 43 also serves to transport the battery 41.

Intr-o alta varianta constructiva o aeronava 50 utilizează un stilp vertical 51, inclus intr-un cadru 52 si care face legătură intre blocul energetic 5 si un suport 53, ca in figurile 8, 9 si 10. Pe stilpul vertical 51 este fixat un scaun 54 pe care sta așezat un pilot 55. Pilotul 55 isi sprijină picioarele pe suportul 53. Aeronava 50 utilizează aceleași rotoare anterioare 2, mediane 3 si posterioare 4.In another constructive variant, an aircraft 50 uses a vertical pole 51, included in a frame 52 and which connects the energy block 5 and a support 53, as in figures 8, 9 and 10. On the vertical pole 51 is fixed a seat 54 on which a pilot 55 sits. The pilot 55 rests his feet on the support 53. The aircraft 50 uses the same front 2, middle 3 and rear 4 rotors.

Intr-o alta varianta constructiva o aeronava 60 utilizează cite o protecție 61 pentru fiecare grup de rotoare anterioare 2, mediane 3 si posterioare 4, ca in figura 11. Protecțiile 61 înconjoară la exterior acest grup si sunt montate simetric pe brațele principale 9, avind forma ce poate fi considerata ovala. Protecțiile 61 au rolul de a proteja pilotul 55 si personalul de la sol in cazul dezintegrării unor rotoare anterioare 2, mediane 3 si posterioare 4.In another constructive variant, an aircraft 60 uses one protection 61 for each group of front 2, median 3 and rear 4 rotors, as in figure 11. The protections 61 surround this group on the outside and are mounted symmetrically on the main arms 9, having the shape that can be considered oval. The protections 61 have the role of protecting the pilot 55 and the ground staff in case of disintegration of the front 2, middle 3 and rear 4 rotors.

Claims

demand

1. Individual aircraft with vertical take-off and landing of the type with multiple rotors, having distributed electric propulsion and where the center of gravity is located below the center of pressure, characterized by the fact that an aircraft (1), individual, with take-off and landing on vertical, uses an energy block (5) as the central part for fixings, which simultaneously supplies energy to the distributed propulsion system of the aircraft (1), and the energy block (5) is constituted as a very rigid and robust part and contains some electric batteries , a control system for them and a control system for the propulsion system of the aircraft (1).

2. The aircraft as in claim 1, characterized in that it is propelled by six rotors, of which two front (2), two median (3) and two rear (4), which are symmetrically attached to the energy block (5), and each front rotor (2) is driven by a front motor (6), and each middle rotor (3) is driven by a middle motor (7), and each rear rotor (4) is driven by a rear motor (8), and each middle motor (7) is fixed on the energy block (5) by means of a main arm (9), and on each main arm (9) a front arm (10) and a rear arm (11) are fixed, and each arm front (10) supports the front engine (6), respectively the front rotor (2), respectively, and each rear arm (11) supports the rear engine (8), respectively the rear rotor (4), respectively.

3. Aircraft as in claim 2 characterized by the fact that the plane of rotation of the middle rotor (3) is located below the plane of rotation of the front rotor (2) and the rear rotor (4), respectively the plane of rotation of the front rotor (2) and that of the rear rotor (4) is superimposed on a certain portion over the plane of rotation of the middle rotor (3).

y

4. The aircraft as in claim 2 characterized by the fact that on the energy block (5) a frame (13) is fixed by means of a vertical pole (12), which supports a pilot (14), and the pilot (14) stands in the position in legs supported on a support (15), and below the support (15) a landing gear (16) is fixed, and the landing gear (16) is preferably constructed of two bars (17), curved downwards and which are crossed , and on the main arms (9), respectively on one side and on the other of the pilot 14, two protective shields (18) are fixed symmetrically, which have the role of protecting the pilot (14) in the event of the disintegration of some previous rotors (2), medians (3) and posterior (4).

5. The aircraft as in claim 2, characterized in that an aircraft (30) uses two vertical pillars (31), included in a frame (32) and which connect the energy block (5) and the support (15), the pilot ( 14) standing in a standing position supported on the support (15).

6. Aircraft as in claim 2, characterized in that an aircraft (50) uses a vertical pole (51), included in a frame (52) and which connects the energy block (5) and a support (53), and on the vertical post (51) a chair (54) is fixed on which a pilot (55) sits, the pilot (55) resting his feet on the support (53).

7. The aircraft as in claim 2 characterized by the fact that two joysticks (15) used for controlling and maneuvering the aircraft (1) are symmetrically attached to the side parts of the energy block (5).

8. The aircraft as in claim 4 characterized by the fact that in case of total failure the pilot (14) can use an ejectable parachute (19), attached to the back of the pilot (14).

9. The aircraft as in claim 1 characterized in that an energy block (40) contains a number of batteries (41), portable and clip-on, the batteries (41) can be quickly replaced when they are discharged, and

each battery (41) can be tipped on a shaft (42) being actuated by a miner (43), the miner (43) also serving to transport the battery (41).

10. The aircraft as in claim 2, characterized in that an aircraft (60) uses one protection (61) for each group of front (2), median (3) and rear (4) rotors, which surrounds this group on the outside and it has a shape that can be considered oval, the protections (61) being mounted symmetrically on the main arms (9).