ES1299492U - Supplementary lift arrangement for vertical takeoff and landing airplanes (Machine-translation by Google Translate, not legally binding) - Google Patents

Abstract

Complementary support system for vertical takeoff and landing aircraft that uses a complementary pneumatic energy system during takeoffs and landings, and is characterized in that it comprises: Compressed air bottles or air containers or containers in the wings, in the tail cone, in the lower or cargo area, on the passenger floor support, instead of the beams, spars, bulkheads and on the keel, for use during the initial takeoff phase and at the end of the landing, by means of a distribution installation or ducts and some solenoid valves and blowing the air: a) Through some holes or slits (3) from the lower surfaces of the aircraft, b) Through some injectors (3b), blowing the air through some air blowing injectors on some inclined deflector plates and c) By some injectors (3b) and by action turbines on other supporting devices. (Machine-translation by Google Translate, not legally binding)

Description

DESCRIPTION

Complementary lift system for vertical takeoff and landing aircraft Technical sector

In support systems for manned and unmanned aircraft, drones, etc. both electric and internal combustion.

The object of the invention consists of:

Use a simple, useful and safer system to carry out vertical takeoffs and landings of airplanes.

Avoid the current problem whereby aircraft do not have enough power to perform VTOL (vertical takeoff and landing) with the engines used in propulsion, making it necessary to use others with greater power, which increases excess weight and does not long flights can be made or with the necessary load.

Apply complementary lift using the energy of compressed air stored in bottles, in tanks in the wings or in the aircraft structure, to send jets of air, which can be used: a) by blowing it directly downwards from holes or slits from the lower surfaces of the aircraft, b) applying them on inclined deflector plates, c) driving turbines that in turn drive other lifting devices during initial takeoff and at the end of landing. The turbines may drive or support propelling fans, the periphery of sustaining fans, or blowers or radial-blade fans that drive air tangentially down the sides of the aircraft fuselage. One of these turbines could be used to drive an electrical generator in an emergency. All these elements can be applied separately or combined with each other. After takeoff, the bottles or containers integrated into the aircraft are filled with pressurized air during the flight by means of compressors or using air from the compressors of the gas turbines.

The bottles and the rest of the structure used do not represent a significant load to continue the flight. In addition to the bottles, portions of the wings, the tail of the plane, the lower or cargo area, the support of the passenger floor, beams, spars, bulkheads and in some the keel are mainly used as containers or containers. In all cases, a volumetric shape is applied to them to act as pressurized air vessels. In the case of stringers, beams, etc. they are given a tubular or hollow rectangular section shape.

The amount of compressed air that can be transported in the planes and in the tail and lower part of the aircraft fuselage is very important. And without having to add large weights in the modifications. The wings could be made monocoque type without beams or spars.

The deflector plates retract automatically when moving the aircraft horizontally or by means of an actuator or electric motor.

The use of vertical takeoff can be extended in all aircraft without limitation by size or weight.

It is possible to use this complementary system as the only one for the initial ascent and then carry out the level flight with the corresponding lift creation. Likewise, only this system can be used for the final descent.

In case of emergency, the nitrogen oxygen bottles that are used can also be used as sustainers.

Unlike other gases such as hydrogen, air is not dangerous.

Background of the invention

Gyroplanes do not perform vertical takeoff. Helicopters fly at low speed, their rotor is dangerous, and VTOL aircraft have poor safety and make very poor use of the energy of engines or turbines at low altitude and low speed. Reason why the use of these planes for commercial flights is not extended. Limited mainly to military-type flights and with many restrictions, in small, short-haul planes or in drones.

EXPLANATION OF THE INVENTION

Problem to solve.

Vertical takeoff aircraft are currently not sufficiently developed, their use being limited to small aircraft and the military field.

The complementary support system for vertical takeoff and landing aircraft uses a complementary pneumatic energy system during takeoff and landing, and is characterized in that it comprises: Compressed air bottles or air containers on the wings, in the tail , from the lower or cargo area, in the support of the passenger floor, beams, spars, bulkheads and in some in the keel, which are used during the initial phase of takeoff and at the end of landing, through a distribution facility or pipes and solenoid valves blowing the air:

a) directly downward from holes or slits in the lower surfaces of the aircraft,

b) with some injectors, blowing the air over some inclined deflector plates and

c) with some injectors, blowing air over some turbines that in turn drive other supporting devices. The turbines can drive supporting rotors or propellers, at the periphery of supporting fans (fans) or tangential blowers with radial blades that drive the air down the sides of the fuselage.

All these elements can be applied separately or combined with each other.

In addition to bottles, compressed air can be stored in containers or containers, mainly inside the wings, the tail cone of the plane, the lower or cargo area, or in the support structure of the passenger floor: beams , spars, bulkheads and in some the keel, which are used as hollow structures with circular, oval or rectangular sections, which store pressurized air

The generated lift is complemented by the main lift and as you go up it decreases and in the end the main lift or wing of the plane takes full charge of that task. On landing, this complementary additional lift increases until that due to the aerodynamic surfaces disappears as the plane's horizontal speed does so, leaving only that of the main fans or turbines of vertical lift. Supplemental lift may be sufficient to perform all of the aircraft's lift.

As soon as the climb begins, horizontal thrust can be applied so that the normal lift obtained with the wings is quickly achieved.

The direct impulsion of the air is carried out by blowing the air through holes or slits. It can also be deflated by blowing air over pairs of inclined plates that redirect it downwards. The type of device used as a pressurized air store and the area used depends on the type and size of the aircraft.

The compressed air is partially discharged, leaving air for a possible descent in an emergency and during the flight they are recharged with compressed air from the aircraft system or using compressors if higher pressure is desired, applying energy from the aircraft. Also in an emergency, oxygen bottles can be used if they are carried and if there is no danger of fire. And in more severe cases it could be landed using a standard runway system.

Brief description of the drawings

Figure 1 shows a schematic and plan view and partially sectioned of an aircraft with the bottles and a support system of the invention.

Figure 2 shows a schematic and perspective view of a wing portion.

Figure 2a shows a schematic and perspective view of a portion of the structure of a semi-monocoque fuselage.

Figure 2b shows a schematic and perspective view of a tail portion of an aircraft.

Figure 3 shows a schematic and sectional view of a wing with a system of air-inflating holes or slits.

Figure 4 shows a schematic and sectional view of an insufflation head which divergently spreads the air in the form of a fan.

Figure 5 shows a schematic and sectional view of an inclined baffle plate and the insufflator injectors.

Figure 6 shows a schematic, sectioned and insufflating view of a pair of inclined baffle plates and the insufflating injectors.

Figure 7 shows a schematic and sectional view of a pair of curved and inclined deflector plates and the insufflator injectors.

Figure 8 shows a schematic and sectional view of a pair of inclined deflector plates and the insufflator injectors by means of artichokes.

Figure 9 shows a schematic and plan view of a supporting fan with peripheral fins to which the flow of two tangential injectors is applied.

Figure 10 shows a schematic and plan view of a turbine or rotor with rotating blades that rotates when air is blown through the slits or slits on its trailing edges.

Figure 11 shows a schematic and plan view of an aircraft with the turbine or rotor with lifting blades. These extend when applying a turning movement and at the end they are collected by the action of a spring, being housed in the existing channel along the fuselage. Add a system of photovoltaic panels.

Figure 12 shows a schematic view of a portion of the rotor with the impeller turbine and the insufflator injector.

Figure 13 shows a schematic and sectional view of the fuselage of an aircraft with two lift tangential turbines on its sides.

Figure 14 shows a schematic and plan view of an aircraft with a vertical takeoff system showing pairs of tangential lift turbines applied to an aircraft.

Preferred embodiment of the invention

Figure 1 shows the aircraft (1) with the compressed air bottles (8) and its distribution installation (18). Whose air drives the faults (fans) sustainers (7c). Add the electric fans (fans) (6s) for horizontal stabilization of the aircraft. Engines or propelling fans are not shown.

Figure 2 shows a portion of the wing (2) with its beams or spars (2v).

Figure 2a shows a portion of the fuselage with the beams or spars (2v), the bulkheads (1m) and the fairings (1c).

Figure 2b shows the tail of an aircraft where part of the tail cone enclosure can be applied as a pressurized chamber.

Figure 3 shows the wing (2) with the air insufflating holes or slits (3) that generate a reaction and additional lift of the wing.

Figure 4 shows the air insufflating head (3a).

Figure 5 shows the injector (3b). which blows air into the lower area of the inclined plate (4), deflecting the air downwards and generating lift as a reaction.

Figure 6 shows the pair of injectors (3b). that blow air into the lower areas of the inclined plates (4), deflating the air downwards and generating

lift as a reaction.

Figure 7 shows the pair of injectors (3b). that blow air into the lower areas of the curved inclined plates (4). deflating the air downward, and generating lift.

Figure 8 shows the pair of artichokes (3a). that blow air into the lower areas of the inclined plates (4) deflecting the air downwards. and generating lift as a reaction.

In figures 6, 7 and 8 the pairs of baffle plates have their inclination reversed with respect to each other.

Figure 9 shows the supporting fan (7c) that carries the peripheral fins (5t) to which air is injected through the tangential injectors (3t). rotating the lift fan and generating lift.

Figure 10 shows the rotating propellers (7t) blowing air through slits or slits (3f) at their trailing edges, generating a reaction of the blades and as a consequence providing lift.

Figure 11 shows the aircraft (1) with the turbine or rotor (7) of lifting blades. Pressurized air is blown into a turbine which turns the blades. The latter is not shown in the figure. Add some photovoltaic panels (9) on the wings and horizontal tails. Propeller motors or fans are not shown.

Figure 12 shows the blower injector (3b) that blows the air that drives the turbine (5) and this to the rotor (7).

Figure 13 shows the aircraft fuselage (1) with two supporting tangential turbines on its sides (7t) driven with the same axis by the turbines (5) driven by the flow of some injectors not shown in the figure. The arrows show the direction and direction of the airflow.

Figure 14 shows the aircraft (1) with the wings (2) rotating, adopting the vertical displacement position, with the pairs of complementary tangential lift turbines (7t), driven by the turbines (5), applied to the sides of the fuselage. and the turbines or propelling fans and main stabilizers (6sp).

Claims (11)

1. Complementary support system for vertical takeoff and landing aircraft that uses a complementary pneumatic energy system during takeoff and landing, and is characterized in that it comprises: Compressed air bottles or air containers or containers in the wings, in the tail cone, in the lower or cargo area, on the passenger floor support, instead of the beams, spars, bulkheads and on the keel, for use during the initial takeoff phase and at the end of the landing, through a distribution installation or ducts and some solenoid valves and blowing the air: a) Through some holes or slits (3) from the lower surfaces of the aircraft, b) Through some injectors (3b), blowing the air through some air blowing injectors on inclined deflector plates and c) By some injectors (3b) and by some action turbines on other supporting devices. 2. Support system according to claim 1, characterized in that the interaction devices with the turbines (5) are supporting blade rotors (7), fans/fans (7 c) or tangential blowers (7t) with radial blades of air supply downwards on the sides of the fuselage. 3. Support system according to claim 2, characterized in that the fans and blowers are applied in combination with each other. 4. Support system according to claim 1, characterized in that the support structure of the passenger floor, the beams, the spars, the bulkheads and the keel of the aircraft, are used as hollow structures of circular, oval or rectangular section to store the air under presure. 5. Sustaining system according to claim 1, characterized in that it comprises compressors for recharging or recovering the compressed air used. 6. Support system according to claim 1, characterized in that the inclined deflector plates (4) are automatically retractable. 7. Support system according to claim 1, characterized in that the pairs of deflector plates have their inclination inverted with respect to each other. 8. Sustaining system according to claim 2, characterized in that the fans/fans (7c) have peripheral fins for impinging air from the turbines. 9. Support system according to claim 2, characterized in that the rotating blades of the rotors (7t) carry slits or slits (3f) on their trailing edges to generate the reaction of the blades and as a consequence to provide lift. 10. Support system according to claim 1, characterized in that it has divergent air insufflation nozzles. 11. Support arrangement according to claim 1, characterized in that the upper surfaces of the fuselage and wings carry panels of photovoltaic cells.