DE2344215A1 - AIRCRAFT - Google Patents

Description

S 16 P 71

Applicant: Short Brothers and Harland Limited

Airport Road, Belfast, Northern Ireland 2344215

Aircraft

The invention is concerned with plug devices and proposes an aircraft which is characterized by a device body having a channel, the longitudinal axis of which extends through the body, by flow generators for generating an ambient air flow through the channel from an inlet end to an outlet end for the purpose of generating one along the axis of the channel acting thrust, and by control means for varying the position of the device without Umrichtung or essential Umrichtung of thrust, whereby the apparatus for controlled flight of a starting position, in · that the axis of the channel vertically or substantially ■ * - is vertical _vi is suitable in a forward flight condition in which the axis of the channel is opposite the vertical

is inclined, with two wings on the outer surface of the ^s -, · body are provided, which on both sides of the body ^f ! are arranged and no or essentially no V- ■ · '. »_,

Position. .. , _% '·' ■ «·

. ' . ■% '■■■'

.- '' ·, · The invention is hereinafter referred to in the drawings " · -, -

'-, - illustrated embodiment explained; in the drawings _r -fi .j / li ',. '* "

. ihungen shows: '-)% ' - '

40981 1/0 ^ 94

23U21S

Fig. 1 is a front view of the aircraft according to the invention in starting position;

FIG. 2 shows a side view of the aircraft according to FIG. 1, partly in section;

3 is a top view of the aircraft according to FIGS.

1 and 2;

Fig. 4 is a perspective view of the in Fig. 1,

2 and 3 shown aircraft, partially in section;

5 shows a plan view of a fuselage for an aircraft with a different arrangement of the wing;

6 shows a rear view of a device fuselage for an aircraft with a different wing design; » _{

FIG. 7 shows a plan view of the device body according to FIG. 6.

An aircraft in the form of a drone (e.g. target display, aircraft) has a fan 1 with fan blades

la is equipped and is driven by an internal combustion engine 2, ^J: '' for example a piston engine or a turbine engine, ■;, - _r , the fan being arranged symmetrically in a $ '■ ' cylindrical duct 3, which is surrounded by a % '' - ^, i, annular jacket h is defined, which is the trunk

■ fr.,.

· '- ", *,", -. · Of the device. The fan 1 and the motor 2 are

': "fj, held in the channel 3 by radially extending arms 5,

^ j -I '

/ ι,

23AA21

the motor 2 being arranged above the fan 1 and the fan 1 rotating about the longitudinal axis A of the duct 3. On the jacket 4 legs 6 are arranged, which support the device on the ground or a load base, and although in such a position that the longitudinal axis A of the channel 3 extends vertically. A fuel tank (not shown) is accommodated in the aerodynamically shaped nose tip 7 above the motor 2.

-v, i.

As can be seen from Fig. 2, the jacket 4 is double-walled and has the profile of a wing in cross section. When referring the blower 1 in operation are drawn ambient air'wirkt be-in the inlet 8 of channel 3 and that this hindurchstromt through the channel 3 and Z ¹ exits the channel 3 from the outlet 9, so that a - ''", -Lift thrust or a feed is generated.

The front part 4a of the shell 4 is in the axial direction

-Jr

seen shorter than the rear part 4b, so that when the axis _w A of the channel is vertical, the plane of the channel inlet is inclined downwards towards the front part 4a of the shell 4. This prevents the air from entering when moving forward

flight favors.

The upper edge surrounding the inlet end 8 of the channel 3, des The jacket 4 has smooth contours, so that a smooth air flow ^

/.0981 1 / CU94

is guaranteed through the jacket into the inlet. Depending on the construction of the device, the diameter of the channel 3 at the outlet end 9 can increase or decrease.

Transversely over the outlet end 9 of the channel 3 extend Control surfaces. These are in the form of a slope control surface 11 extending across the outlet end 9 of the channel 3 extends laterally from one side to the other and which is pivotable about its first axis. Two roll and yaw control surfaces 12, one on each side of the pitch control surface 11, run in the right Angle to this. The control surfaces 12 are around a second Axis that is perpendicular to the first axis, pivotable, and they are for the roll control and the Yaw control can be moved individually as well as symmetrically.

However, each control can be replaced with a set of small control elements that are both symmetrical as well as individually movable.

On opposite sides of the shell k wings 13 are provided which form a complete support surface of the device _t . As shown in Fig. 2, these blades 13 have strongly swept leading edges and normal to the air flow -

-5 4098 1 -1 / UA = OA .; ^

Trailing edges as with a delta wing, and the pitch control surface 11 extends along the trailing edge of the entire wing. When the device stands on its legs 6 in such a way that the axis A of the channel 3 runs vertically, - ', - the wings 13 lie in one and the same vertical plane and consequently have no V-position. The vertical plane in which the wings 13 lie is opposite the
Axis A of the channel offset. The wings 13 are still flat, and both surfaces of the wings 13 are flat. Alternatively, the wings can have the cross-section of an airfoil. The entire airfoil formed by the wings 13 has a low aspect ratio, which is preferably less than three.

A series of radial stator blades I ¹ I, which is arranged below the fan blades la, serve to remove eddies from the air flow flowing through the duct 3 and thereby reduce the tendency of the device to rotate about the axis A of the duct. Another control option to prevent this rotation is provided by the
Control surfaces 12. Instead of the stator blades Ik can also. a fan rotating in the opposite direction can be used.

The control surfaces II and 12 are actuated by actuators 15 ^ actuated, of which only two are shown in Fig. 2,

A038 11 / GA9

il and the actuators 15 are from an electro-mechanical they, control unit actuated (not shown) - the one

ir 'receiver from a remote transmitter

• ^ receives radiated control signals and controls the actuators 15 according to their stipulation t P ^ lä ^ clie. The electronic control unit% _{i; fj} f is also used to control the fan speed to M and it can be used in the double-walled construction of the | Sheath 4 be housed.

As can be seen from Pig, 2, the longitudinal axis B of the motor 2 is inclined with respect to the axis A of the channel 3. This ensures that the center of gravity is displaced the device from the axis A de3 channel 3 away from a later to be explained basically forward, in such a way that the aerodynamically shaped nose 7 more in alignment with the air _stream's entering the channel. In addition, the motor 2 is arranged above the fan 1 in order to shift the center of gravity of the device upwards so that it is in the area of the plane of the inlet end 8.

In operation, the motor 2 rotates the fan 1 will call whereby a flow of ambient air through the duct 3 through hervorge- \ which produces a vertically acting propulsive thrust, which lifts the device from the ground or the load base. The remote transmitter then delivers a ψ.

098 1 1 / CU "9

Vo

23U215

^ 'Ssolisignal to operate the control surfaces 11 and 12 Äio- ^ let the device be tilted. Because Sw ^ r * - ^ ki unkttdes device is moved, the Required to trim the \ ^ device forces are reduced. In commanding ^ r by Γ "'^ orne tilted position, the axis of the channel, and I ^{x is} the direction of action of the drive thrust against the Verti- I icale inclined, so that the device forward and naca ubeu T fgetrieben is. The arrangement of the channel inlet end 8 is so fu met that when the device moves forward with a large adjustment f "i-", the air flow easily flows into the channel 3 ι ⁴ * .

_S is I fßemerkt that because of the smooth shaping of the upper edge of the shell S produces the air flow over this edge a suction effect \, which thus generates lift on the jacket. 4 X Since the center of gravity of the device is also in the area of the inlet end 8 of duct 3, the drag moment force caused by the sucking in of air into duct 3 acts through, or almost through the center of gravity, whereby ¹ any essential moment effects are suppressed, I _d They originate from this power of resistance and might endeavor to twist the rotation to _a and make it more difficult to control it.

1% ^ - further forward flight work through | he forward movement _; , the aerodynamic forces caused by the device on the jacket M

09811

and generate buoyancy, thereby reducing the behavior of the device Hand in hand with the increasing forward speed increasingly determined by the slope control surface 11 in order to bring the axis A of the channel 3 almost to the horizontal, for example in a position of 10 opposite the horizontal. In this position, most of the drive thrust is used to move the device to drive forward and the maximum speed in level flight is reached.

The device can land and take off vertically, and the plug- _Ψ PSfeJjl ψ

The range extends continuously from zero speed to maximum speed, including lateral and backward speeds are achievable. The device can also perform dives, and a Maximum speed would be achieved in a dive.

The continuous plug area results from the fact, * - '', that the main source of lift and propulsion thrust, namely, the fan 1, at all speeds buoyancy and · _ thrust supplies, the employment of the device in increasing; The extent to which the forward speed increases. _} |.

When the device moves forward, use the outer _a »

area generates the device aerodynamic forces, and these ^ J on the fuselage and the wings generate lift forces. Now if the device speed increases,

A09811 / 0A9A

23U215 .it

the aerodynamic forces grow and strengthen it, that To tilt the device increasingly against a horizontal position, whereby a larger proportion of the drive thrust is used will drive the device in the forward direction because the horizontal component of the thrust is increased.

However, there is no defined transition area _; the situation in which the device is held entirely in the air by the propulsion thrust, to the situation in which it is mainly due to the aerodynamic forces acting ^{on the outside of the jacket 4 and ^ ', T of the wings 13} air * - is held This is due to the aerodynamic forces increase by the gradual An-./-, ii on the outer side of the t Vi. '\.' - £ jacket 4 and the blades 13.

ι \

If the device is flying forward in straight flight or i t Wim Manövrierflug generates the air flow around the shell I ^{"ί / 1 <·} -4 moments on the device. This should means of the control, ^ \ LFFI areas be counteracted by the device in Hold straight ahead or in maneuvering flight.

"'rf

'■ f / ^' The size of the SSE acting on the sheath 4 forces or _t, l $ \ -, moments depends on the shape of the air stream from which moves around in ^ n ^ direction around the cladding H. If the position _k y * \ \ or the speed of the device is changed, it sees ^ - the shape of the air flow around the outside of the jacket 4

- 10 A09811 / OA9A

- 10 -

2 3 A A 2 1

suddenly change, causing a large or sudden change in the forces or moments acting on the device. Such a change in force or torque on the device can be extremely difficult to control, and if so If you fail to control it, the device can become completely unstable and uncontrollable.

,; In this connection, the wings 13 are on both sides

".., ι of the jacket H constructed in such a way that, in interaction with the jacket 4, they have useful forces - and momentary characters -

, j deliver statistics. This is achieved because of one

Wing with strongly swept leading edges generated air flow type shows the tendency to remain uniform over a large range of angles and do not move

\ 'suddenly change, and because of the position and _v the dimensions of the wings 13 in relation to the shell 4

''"· -, can be chosen so that acceptable Gesamtch'arakte- _'\; occur istics For example, the can on this.

H; Device acting slope torques can be selected so that ·>? '' that they are easier to control. This ensures

- "ensures that there is no sudden change in the shape of the '""(;,';i" · - ■> air flow around the jacket, which in turn ensures '"* -: < ν -'» ·, that changes in the forces or moments, ΐ * ί '''·".- *: £"' · which the device depends on the speed

/.0981

23U21

or make changes in position unstable, smaller and occur more gradually, thereby easing the problem of controlling the device.

In the device shown in FIGS. 1 to H , the flights: 13 are arranged on opposite sides of the device fuselage ί, as shown in plan view, and they are in "J" -i - ^. a vertical plane close to the axis of the channel- -'j '"- " These wings 13 can, however, also be ^{offset from the rear c} '"- .- " part i | b of the device body 2, as shown in FIG. ,shown. The trailing edges of the wings 13 can also be designed to be movable and thereby act as control surfaces. If the aircraft flies so that the axis of the "· 'channel horizontally or substantially horizontally comparable 3

■ • 'j runs, you can also see a noticeable amount of lift . "; achieve the delta wings 13.

Although in the embodiment in FIGS. 1 to 4

r the wings 13 have no V-position, they can cioch

■ get a small V-position, for example up to a maximum of about 20 °, and still the device bsi. low speeds and high jobs wix-k-

_: - ~, .-sam stabilize. Although also with vertically running:

,, -Axis A of the channel the wing 13 in a vertical plane lie, they can also lie in a plane which is at an angle of, for example, a maximum of approximately Is inclined 10 ° to the vertical.

409311 / CK94

23U2T5

- 12 -

In another embodiment shown in FIGS. 6 and 7, the trailing edges of the blades 13 extend well below the outlet end 9 of the channel 3 and are connected to one another by a one-piece transverse part 13a which runs transversely to the outlet end 9. The pitch control surface 11 is attached to the trailing edge of the blades 13. The wings 13 also have forward extensions 13b which extend beyond the Einlaföende 8 of the channel 3 and are attached to the fuel tank 7 and the engine 2 receiving central body, forming a full delta shape. Although in the embodiment shown in Fig. 6, the side edge 20 of the extension 13b is swept to the same extent as the side edge 21 of the wing 13 on the side of the shell k , it can also be swept more or less, as shown by the dash-dotted lines 22 and 23 is indicated.

In order to increase the forward speed of the device, the device must increasingly be in a horizontal orientation tilt to increase the horizontal component of the drive thrust. In the case no control surfaces on the outer surface of the shell 4, or at low forward speeds, creates the deflection of the pitch control surfaces 11 in the air flow coming from the duct, a force on the control surface 11, which softens the device

038 11/049

Ui ^23U215

i due to tilting movement. Roll behavior and yaw behavior

• - will; controlled by means of the control surfaces 12, and to float the device ^{if> v} caused by the displacement of the '.--'<"-τ _r H gravity of the device movement is -eiert compen-τ · f ^ ?? 7λ that you deflect the slope control surface 11 in the air flow ^ YES! But if on the outer surface of the shell 4 outer ("'Ι''''Tsteuerflachen are provided, you can tilt, the ι , ^v % roll behavior and the yaw behavior at higher speeds' control by using the 7 outer control surfaces to control the aerodynamic forces acting on the jacket.

Note _f that _s although the control surfaces shown as I are that they extend transversely calibration laterally to Cantilevered 9 of the I channel, te it υ across a K of the outlet 9 may be arranged, if bf provided ielsweise the Au3laß with a flat edge it is rectangular.

The thrust available for the device can be viewed in two parts, namely the gross thrust,

■>4; x _t ^ which is generated by the fan 1, and the torque resistance

% Λ * ί [stood the intake air. These two components work ³ ' ί at an angle to each other, depending on the position

^r Ί

^{4 of} the device opposite its plug path through the air. if

, V; the gross thrust is noticeably greater than that for the previous 4

ί ^c drove the unit Isur available net thrust can

S ₁ '

IiV ^ξ 4098 1 1 / 0Ä94 - ιή -

Ill

' - It -

'Liiin be achieved noticeable lift from the vertical ■ iomponenten the gross thrust Without thereby ^ horizontal component would be greatly reduced. If so.it & ■ ensures that a reasonable overall performance Äiinsichtlich is present for the production of the net thrust er-1, 'lorderUchen energy, and when the "leaving flow ^ H velocity of the air by" en passage 3 relatively. · _G Ross , large buoyancy forces can be generated with little energy, which essentially carry the device.

The low energy required to drive the fan and the low pressure ratio across the fan are achieved by using a large mass flow rate. The one from de. Fan drive thrust produced is therefore supplied in that one large "assenstromungsgeschwindigkeiten the air used as vxel _ra ore a high air flow rate. By increasing the diameter of the channel towards the outlet end 9, downstream of the fan 1, the air can expand inside the fan so that more air can be sucked in. Characterized the Massenströ.ungsgeschwind.g- W ^m ~ \ ikeit the air is increased appreciably through the channel.

* ^: although it was mentioned above that in order to increase the ■ forward speed of the machine, the machine is tilted.

Q 9 8 11 / 0-94

- 15 -

to _? To increase the horizontal thrust component, it is important that this component can also be increased by increasing the energy output of the fan 1.

JCreate further control of the propulsion thrust generated by the air flow through the anal ^Y $ 3 can erleichen characterized in that a variable outlet area fax de. "Provides channel, in such a way that the outlet surface ^ er. Is increased or decreased. This can be done, for example, by providing the jacket at the outlet end = 9 of the channel with segments that can be pivoted inwards or outwards, or by arranging a conical central body movable in the axial direction in the outlet, or by provides a flexible liner around the outlet end 9 of the channel 3.

Although the device was explained using the exemplary embodiment of a drone, it can also be used for manned flight be.

The device of the present invention with the lateral

iW '^^ k ^^ m ^ P ^^^ ^ ant ^ ila ^ piorgera ^ n- or:; _if "^^ Pl ^ || y ^ rä | a without such WeJ,. VortMle;>. namely:

i \ f

4i "^ i * 4 098 1 1/049

23442Ί5

- 16 -

1. The wings can be arranged to be acceptable Generate incline torques over a large adjustment range of the device.

2. The wings provide greater performance in forward flight with them, thanks to the extra buoyancy they create.

V i The device can be viewed as a summary ¹ Tu χ *

a jacketed rotor, which has good operating behavior in the ι <"■ ',,

Hovering and at very low speeds - '

shows, and a delta wing or a wing with a low j

Aspect ratio, the good performance at higher ,: ι ί ¹

Shows speeds. The device is thus able to. , _t [ over a wider range of forward airspeed% ψ ', can operate satisfactorily from zero upwards. __ ' ■ -. ^] \

The device has other considerable advantages in comparison * '"

to devices with non-jacketed rotors, namely insofar as

as: j '''.

(a) the diameter of the fan can be kept small -,.

because of the beneficial effect of the mantle on the

i 'i

from the fan at low and vanishing forward 7 speeds generated thrust. .,, u.

- 17 -

409811/0494

-If-

(b) the device is not subject to any speed restrictions, as is the case with helicopters because of the relative high forward speed of the previous sheet is the case.

(c) the device with its small diameter fan basically is suitable for higher speeds.

W (d) caused by the mass of the blower rotation '_' ^ energy is small, the propulsion thrust during landing so that almost

can be made to disappear instantly by turning off the engine. This simplifies that f Landing problem of the device, especially a drone - 'strong wind.

, '· -' ... (e) the jacket around the fan the fan blades in front of it , "protects against being in contact with any external surfaces

come. Rolling over while landing does not necessarily mean serious damage and danger for; the operating personnel are reduced. This is be-) Sonder important when the device is used as a drone.

the device, since its fan is encased, in a network , - '' "'can be landed. This is particularly significant when the '' The device is used from the sea.

- 18 4Q981 1/0494

Claims (1)

- 18 - 23AA215 Claims 1, plug device, characterized by a device body with a channel (3), the longitudinal axis of which extends through the body, through flow generator (1) for generating an ambient air flow through the channel from an inlet end (8) to an outlet end (9) for the purpose of -. ₂ ■ generation of a thrust acting along the axis of the duct, ~ 'i - and by control means (11, 12) for changing the position, -' of the device without converting or substantially converting the Thrust, which makes the controlled flight device out of a / Take-off position, in which the axis of channel 3 is vertical or Λ 'essentially vertical, in a forward flight ! ' ; is a suitable state in which the axis of the channel is opposite- '■'; {'' ' is inclined above the vertical, with two wings (13) are provided on the outer surface of the body, which are arranged to _: ^T ': .. both sides of the body and none or Γ.' have essentially no V-position. *, 2. Apparatus according to claim 1, characterized in that the V-position is not greater than 20 °. ι ■■ ί 3. Apparatus according to claim 1 or 2, characterized in that the wings together form a complete support surface for 'the device, and that the complete support surface has a low aspect ratio. - 19 40981 1/0494 ^ JiJ Λ ~ H 23A4215 - 19 - ll. Apparatus according to Claim 3, characterized in that the entire wing of the apparatus has an aspect ratio of less than three . 5. Device according to one of the preceding claims, characterized characterized in that the wings have a strongly swept front edge. 7g- ^ f> v _{6 # device according to} one of claims 1-5, characterized . ^> ^: |; ^ · | Ί draws that each wing has an extension, ^% 5? | L which extend beyond the inlet end of the channel _ ;; ~ iii " ⁴ ι extends. & y. Apparatus according to any of claims 3-6, characterized labeled in _{f> i} characterized in that the complete support surface of the apparatus' Delta Delta form or supported shape. .8th. Device according to one of the preceding claims, characterized in that the wings are flat. "9. Device according to one of the preceding claims, dadurcß ■ characterized in that the trailing edge of each wing stitch extends beyond the outlet end of the channel. 10. Apparatus according to claim ^ or one of claims 7 "9, ^ as far as dependent on claim 6, characterized by a central body to support the flow generator, 409811/0494 " ²⁰ , DTS Ii W * - 20 - each of the mentioned extensions being connected to the central body. 11. Device according to one of the preceding claims, characterized marked that the wings have no V-position and that if the axis of the duct is vertical or substantially vertical, the wings are vertical in the same Lie level. 12. Apparatus according to claim 10, characterized in that said vertical plane is offset with respect to the channel axis is. 13. Apparatus according to any of the preceding claims, characterized in that both wing surfaces are flat. 14. Device according to one of claims 1-10, characterized in that that each wing has a wing cross-section, 15. Apparatus according to any one of the preceding claims, characterized in that the controller has a first pivotable arranged aerodynamic control surface, which is located at the outlet end of the channel so that the through Air flow flowing through the duct acts on them. 16. Apparatus according to claim 15 when dependent on claim 3, characterized in that the first aerodynamic 0 9 8 1 1 / CU94 - 21-- I ₂₁ . V 23-215 The fire runs across the trailing edge of the complete Support surface of the device extends. Wif. Device according to claim 15 or 16, characterized in that the controller has 2 second pivotably mounted aerospace having dynamic control surfaces which fsamen on a Community / swivel axis are arranged, extending transversely to the f "{pivot axis of the first aerodynamic Steuerflächp ER ^ stretched, and the 3ind so located at the outlet end of the channel, | that the air flowing through the channel air flow acts on them, the second aerodynamic control surfaces being pivotable individually or symmetrically. 18. Apparatus according to claim 1 ^T , characterized in that the second aerodynamic control surfaces are arranged on opposite sides of the first aerodynamic control surface. I ₉ . Device according to claim 17 or 1S / V / urch, characterized in that the pivot axis of the first aerodynamic control surface runs perpendicular to the pivot axis of the second aerodynamic control surfaces. Λ V 20. Device according to one of claims 16 to 19, characterized in that that at least one of the first and second aerodynamic control surfaces has a set of control surface |. '^ ^Λ 40981 Ϊ / 0494 - 22 - Has elements that are symmetrically or individually ^ pivoted. 'M ;, '21. Device according to one of claims 16 to 20, characterized in that ⁷ % - '', -, indicates that the controller also has a receiver J / ^ has> from a remote transmitter. " ' χ , receives radiated control signals and according to the same, 'w output signals generated, and by an actuation system, ■ m- with the help of which the aerodynamic control surfaces fe; Controlled according to the output signals of the receiver I; will. i 22. Device according to one of the preceding claims «thereby characterized in that the flow generator is a fan and i comprises a motor driving the fan. s 23. Apparatus according to claim 22, characterized in that the Fan rotates around the axis of the duct, and that the motor is located above the fan. 2k, device according to claim 22 or 23, characterized in, ξ. that the center of gravity of the device is shifted from the axis of the duct, f, towards the front part of the body. Γ - -'23 4098 - 23 - '"^^ 23'. Device according to one of claims 22 to 2 ^l \, characterized : M0S ■ ''(' - ^ indicates that radially stator blades are provided in the duct between the fan and the outlet end of the duct. _Ä '| 26. Device according to one of the preceding claims, characterized ■ 4 indicated that the plane of the inlet end of the channel % ^ is inclined with respect to the axis of the channel, whereby if "■ 'Ä '"? the axis of the channel is vertical or essentially vertical ', ; kal runs, the plane of the inlet end is inclined downwards with respect to the., / front part of the body. 27. Device according to one of the preceding claims, characterized characterized in that the device body is a tubular jacket with a wall which is shaped like an airfoil in cross section is. 28. Device according to one of the preceding claims, characterized in that the channel is cylindrical. 29. Apparatus according to any one of the preceding claims, characterized in that the outlet end of the channel is circular. W ' ¹⁴ ' Ά ψ- -'.'- '■' ■ ■ - ■ ■ ^i; 'g: .piÖ ^ | Ger; ät - according to one of the preceding. Claims ,, ^ characterized by "% '*"% (teek denotes that the cross-sectional area of the outlet end of the channel is variable. 09811/0494 - 24 - 31c device according to one of the preceding claims, characterized characterized in that the center of gravity of the device is near the plane of the inlet end of the duct. M £ h ~ ^■:; 'f. .'J 1 / Aifli »r -» τ · »-r