Aircraft having buoyancy gas balloon |
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申请号 | EP82305838.3 | 申请日 | 1982-11-03 | 公开(公告)号 | EP0078713A2 | 公开(公告)日 | 1983-05-11 |
申请人 | Ferguson, Frederick; | 发明人 | Ferguson, Frederick; | ||||
摘要 | An airship having a spherical balloon filled with buoyant gas such as helium at a pressure substantially greater than atmospheric and which is mounted for rotation about a normally horizontal axis, the airship including a rigid load supporting yoke having two support arms extending upwardly from a central gondola and each with an upper end rotatably connected to the balloon, is characterized by the gondola and support arms having surfaces close to and conforming to the shape of the balloon so as to inhibit air flow between the gondola and the bottom of the balloon and to redirect this air to the sides and back of the balloon. | ||||||
权利要求 | |||||||
说明书全文 | This invention relates to an aircraft, or airship, in which the major part of the lift is provided by a buoyant gas such as helium. This invention is an improvement on the aircraft described in co-pending European Patent Application No. 80302686.3 filed August 6th, 1980, and which corresponds to U.S. Patent Application Serial No. 64286 filed 6th August 1979. The aforesaid application described an aircraft using a so-called "super-pressure" balloon which is a generally spherical balloon having essentially fixed dimensions and shape when inflated, and which contains the buoyant gas (normally helium) at a pressure sufficiently high that the shape and size of the balloon is substantially unaffected by normal changes in atmospheric pressure and temperature, even when the balloon has little or no internal supporting structure. Further details concerning the nature of super-pressure balloons and the pressures intended for use in such balloons as used in this invention will be found in the aforesaid application. As described in the aforesaid application the aircraft further comprises:-
Rotation of the balloon contributes to the lift by virtue of the Magnus effect,'which becomes effective when the aircraft is moving forward; for initial lift-off engine thrust may augment the static lift. An aircraft having the features described above will hereinafter be referred to as an aircraft "of the type described". The airship described in the aforesaid application had arms and a gondola of airfoil shape,and the arms were curved lengthwise to conform to the shape of the balloon and to position the gondola so that the distance separating the bottom of the balloon from the top of the gondolawas less than 1/10 of the balloon radius; this provides good manouver- ability of the craft as compared to standard balloon construction using cables. The top of the gondola was curved in the longitudinal direction to follow the curve of the balloon down to the fore-and-aft centreline of the craft, beyond which the surface sloped downwards. The present invention provides an airship which has major features similar to that described in the aforesaid application, but in which the arrangement of gondola and supporting arms is modified to improve the flight characteristics and especially the ratio of lift to drag which can be obtained with a rotating balloon. In accordance with the present invention, in an aircraft of the type described, the gondola has a portion of its upper'surface concavely shaped to conform to the balloon surface both laterally and longitudinally and spaced from said balloon surface by an amount small enough to restrict flow of air between the gondola and the balloon when the aircraft is moving in the forward direction. A portion, and preferably a major portion of the gondola upper surface may be situated less than 12 inches (30.5 cm) from the closest parts of the balloon surface. This distance will normally be less than 2% of the balloon radius and may be about 1% for a large balloon (say 160 ft. or 50 m. dia.). The restriction of flow between the balloon and the gondola reduces drag since air which would otherwise flow under the forwardly moving bottom surface of the balloon is deflected under the relatively smooth bottom surface of the gondola. This invention will be described in more detail with reference to the accompanying drawings, in which:-
The main components of the aircraft or airship are as described in my aforesaid application, and are as follows:-
The general details of construction, especially in relation to the balloon material, the means for pressurizing the balloon, the internal cabling to maintain the spherical shape of the balloon, the balloon rotation means, the nature of engines 40, and the general form of the gondola 36 and arms 32 which are provided with rudders 41, are all as described in my aforesaid application. However, the airship of this invention has the following modifications as compared to that of my aforesaid application:-
The amount of Magnus lift will depend on the forward speed of the airship, rotational speed of the balloon, and surface roughness of the balloon. The following table gives calculated figures approximating what would be the optimum flying conditions for three models of airship of the design illustrated herein, and having balloons respectively of 72, 160 and 200 ft. (22, 49 and 61 metres respectively):- It may be noted that the figures for Magnus lift are very approximate pending large scale experiments. It will be seen that Magnus lift can contribute substantially to the net maximum disposable lift, especially in smaller sizes of the airship. As size increases the toal static lift increases with the cube of the balloon diameter whereas Magnus lift depends on the square of the balloon diameter so that relative amount of Magnus lift diminishes. However in the 160 ft. (49 metre) diameter model the Magnus lift is still more than 40% the net disposable static lift. Even in the 200 ft. (61 metre) dia. model the Magnus lift will still be about 30% of the net disposable static lift and certainly over 25%. Since the Magnus lift depends on speed as well as rotation, in order to take off with a load greater than the net disposable static lift either the airship must be made to move along a runway, or engine thrust must be used to augment static lift; the latter alternative is preferred since the ability to hover is considered important. It is anticipated that during take-off the engines will be orientated so that at least 60% of total engine thrust will be directed downwards to augment the static lift during take-off, and the engines will then be inclined to the horizontal position to propel the airship in the forward direction while the balloon is rotated to supply the Magnus lift. Once cruising speed has been reached, the engines will be used primarily only for forward movement. In order for the Magnus effect to contribute substantially to the payload, the engines should be capable of developing downwardly directed thrust which is at least 25% and preferably at least 40% of the net disposable static lift; and the balloon surface characteristics and the means for rotating the balloon will be such that at cruising speed the Magnus lift will also be greater than respectively 25% or 40% of the net maximum disposable lift. The cabling pattern on the balloon may be more complex, and may, for example, give triangular pillowed areas. For this purpose the cables may be arranged in a pattern similar to that of a geodesic dome, or the cabling may be similar to a spherical icosahedron. Also, the blanking effect which is described above may be increased by having arms 32 extended rearwardly and conforming closely to the surface of the balloon. If the gap between the balloon-and the gondola upper surface is very small, air entrained by the surface irregularities of the balloon may be drawn forward through the gap between the balloon and the gondola. If the gap is relatively large, air will flow rearwards under the balloon. It is considered preferable that the gap be at an intermediate dimension so that there is a minimum of air flow between the balloon and the gondola. Wind tunnel tests have been carried out on a model of the airship illustrated in Figs. 4 to 6. The model used a sphere 110 of 12 inches (30.5 cm) having sixteen paddles 112 each 1/4 inch (6 mm) depth, extending over an arc of 90°, and providing surface roughness simulating that produced by cabling in the airship. The gondola 136 of the model was shaped similar to that shown in Figs. 1 to 3, except in having less depth and in having straight sided arms 132. The gondola was spaced from the sphere just enough to clear the paddles, the clearance space being less than 1% of the sphere radius. The following table shows results for the lift coefficient and drag coefficient CL and CD, these quantities being such as satisfy the formulae:
Since the tests were intended to show the effect of various gondola designs on the lift and drag of a particular sphere, the quantity S does not include the gondola area. The tests were made at various spin rates, given as wd, where- u
The results of the following table show that, with the masking effect produced by the gondola, drag can be reduced while lift is increased as the rotation speed of the sphere is increased. |