JPH03503148A - Rapid change wheel landing gear - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention] Invention O name Rapid change wheel landing gear Technical field The present invention provides an alternative for aircraft landing gear, especially helicopters with skid landing gear. Quick change wheel landing gear assembly installed as a system ngewbeelandlng gear assembly).

Background of the invention For helicopters; According to the requirements, surface contact systems of species s are used. For example, helicopter landing systems Systems include skids, skis, wheels, or 70-totes. In these systems, N The energy of the shocks and stresses exerted on the landing gear when it contacts a surface. may include elastic springs, bending rods, threaded rods, air-filled bodies, or various combinations of such damping devices. It is absorbed by the combination.

Under some operating conditions, it is possible to selectively change the structure of the helicopter landing gear. It is highly desirable that

In particular, the Herikogta, which has a skirid landing gear assembly, is very difficult to move aircraft on the ground. It may be necessary to modify it by providing landing wheels for ease of use.

Due to the critical nature of the weight on the helicopter, additional landing skids may be required. Wheel landing systems are undesirable. However, it is not necessary to provide a special structure. It would be desirable to provide a wheel landing system that would rapidly replace the land skid.

i.e. Syskid landing gear instead of Skirid landing gear assembly on helicopters. Alternative wheels that can be quickly installed using the same saddle construction used in the mounting assembly Landing gear assembly required.

Summary of the invention The present invention is configured as a quick-change replacement for helicopter skid landing gear. located on the wheel landing gear assembly. The wheel landing gear assembly is attached to the aircraft's accessory platform. Attach to the helicopter using a saddle with the same structure as used for kid landing gear. Therefore, the present invention does not add any special landing support structure other than a few restraints and brake mounting hardware. provides an alternative wheel landing gear assembly for helicopters. Furthermore, this Rapid replacement wheel landing gear assembly for existing Sugirad equipment equipped helicopters It provides a means for back-sizing the wheel landing system. In other words, these new helicopters require costly and heavy construction to install alternative landing gear. You can make it without using it.

The present invention provides many benefits to skid landing gear systems, including low cost and easy maintenance. It is designed to retain many desirable properties. A pair of front and rear longitudinal tubes It is positioned so that it can be attached to a helicopter saddle used to attach the landing gear. It is attached to a pair of short horizontal pipes separated by a certain distance. Each longitudinal tube is vertical during landing act as an energy absorber for the loads of It acts to stabilize the landing gear. Each longitudinal tube has a front leg attached to it. The front ends are connected to each other so as to be connected to each other. The front legs must be installed so that they can rotate sufficiently. Ru. The nose gear has dual wheels to reduce shimmy. rear main landing wheels , attached to a cantilevered landing gear leg that extends laterally from the longitudinal tube at a location near the aft transverse tube. It is attached. An alternative structure is to attach the main helicopter beam instead of attaching it to the rear transverse tube. Full length rear lateral tube with shorter front and rear tubes with rear ends attached to fittings are used, and resistance restraints are placed from the ends of the front and rear tubes to the vicinity of each rear wheel attached to the side tubes. Made multistable.

During landing, the load on the nosegear is due to the bending deflection of the front and rear longitudinal tubes. more absorbed. Furthermore, the elastic spring of the front leg works with the deflection of the longitudinal tube to generate energy. used to absorb yah. The rear main gear (aftmaingear) Landing loads include elastic springs, bending deflections of landing gear legs and rear transverse tubes, and front and rear longitudinal tubes. or any combination of these actions. Also, the rear main landing gear spring In particular, it is used as a combination bent pipe and truss structure for some operational applications in N land systems. Alternatively, two rear transverse tubes or one transverse tube and a resistance stay may be used.

Normal landing and taxiing loads and vibrations are caused by the landing gear vertical and horizontal tube springs and Absorbs deflection.

As is well known in the industry, there are many different types of springs used in landing gear. is used. However, in the present invention, elastic springs are used and the landing gear O vertical and horizontal tubes are bent. The fatigue stress is completely attenuated along with the stress.

Brief description of the drawing FIG. 1 shows a quick change wheel landing gear assembly according to the present invention installed in a helicopter. FIG. 2 is a perspective view of one embodiment of the invention.

Figure 2 is a perspective view of the quick change wheel landing gear assembly removed from the helicopter. It is a diagram.

FIG. 3 shows an essential part of the invention showing a test bearing support assembly for the aft main landing gear. FIG.

Description of examples Embodiments will be explained with reference to the drawings. Nose wheel landing gear ascend! J (10) is shown attached to the helicopter (11). Ru. Rapidly replaceable nose wheel landing gear! J (10) is the skid landing gear assembly. a structural saddle (12) that is long enough to attach the assembly to the bottom of the helicopter (11); C14) can be used in place of the skit landing gear assembly. It's sea urchin.

Figure 2 shows a quick-change nosewheel landing gear assembly [hereinafter simply a landing gear assembly]. (10) is shown removed from the helicopter (11). landing gear assembly The assemblies (10) extend generally parallel to each other and to the longitudinal axis of the helicopter (11). A pair of longitudinal tubes (16) and (1B) spaced apart from each other are provided.

The anteroposterior tubes (16), (18) are a pair of short transverse tubes (20) spaced apart from each other; (22) is attached.

The longitudinal tubes (16), (1B) and the lateral tubes (20), (22) are well known in the art. They are connected to each other using standard mounting hardware. Landing gear assembly (1 At the front end of 0), the longitudinal tubes (16) and (18) are tapered downward, and the front The legs (26) have an almost vertical axis that rotates around, and the pivot bearing assembles! j (24) is fixed. The front leg (2G) is a pivot bearing assembly! J(24) axis Spring ascender attached to rotate around the line! J (25), connected to @ is attached to the rear arm. Spring ascend! J (25) has front legs ( 26) to absorb vibrations and small deflections to reduce fatigue of the longitudinal tubes (16) and (1B). Reduce load. Furthermore, the front legs (26) are bifurcated to reduce shimmy of the front legs (26). It is equipped with a heavy front military ring.

The aft portion of the landing gear assembly (10) includes cantilevered main landing gear struts (34), (36). ) mounted on the main landing gear wheels (30), (32). Main landing gear strut (34), (36) is attached to the front and back pipes (16) and (1B) respectively, and these 6 pipes It extends laterally adjacent to the rear transverse tube (22). Each main landing gear wheel (3 The landing load applied to 0) and (32) is the deflection of each main landing gear strut (34) and (36), Spring connecting each main landing gear strut (34), (36) to longitudinal tube (16), (18) Elasticity, deflection of the rear horizontal tube (22), twist or twist of the longitudinal tubes (16) and (18) absorbs by any combination of these effects.

Figure 3 shows the connection bracket (38) attached to the rear horizontal tube (22) and the longitudinal tube (18). ) t is shown in a continuous state. Nystomeric bearing (40) is horizontal tube (22) It is attached to the rear tube (18) and bracket (3B). cylindrical elastomer The spring (42) is inserted between the inner surface of the bearing (40) and the longitudinal direction inside the bearing (40). Outside the tube (1B)! It is glued to. The bearing (40) is attached to the rear main landing gear strut ( 36) A pair of legs (46), (46) for attaching t-. Vertical pipe (16) has a similar connection bracket and a branch to attach the rear main landing gear strut (34). Equipped with a Nistomeric bearing.

As shown in FIGS. 1 and 2, the landing gear assembly (10) is mounted on a helicopter C1. 1) It is configured for quick replacement for the suspension landing system. landing gear The horizontal pipe (20L (22) of the landing gear assembly (1α) is the skid landing gear assembly a saddle (12) of the same construction used to attach the helicopter to the underside of the helicopter (11); It is designed to be attached to (14). Or landing gear Asenzo IJ (10), A vertical tube in the longitudinal direction (16 ), (18). In this case, use a sufficiently long rear transverse tube (anteroposterior tube) ( 16) and (18) to stabilize the resistance rods from the ends.

The landing gear assembly (10) features many maintenance-free features of the skid landing system. It is an inexpensive system with The only additional equipment required is the main landing wheels It is a fluid formal system for silencing. The landing gear Asende IJ (10) is The wheel landing gear assembly can be easily integrated into existing ski areas without the need for costly and heavy additional mounting structures. The front landing gear assembly provides a quick replacement means for attaching to the back of the helicopter. Since the landing gear assembly (10) is a skid landing system, the landing gear assembly (10) 9, which eliminates the traditional weight and cost disadvantages that arise when providing wheels for helicopters. eliminate the problem.

Although the present invention has been described above in detail with respect to its embodiments, the present invention still deviates from its spirit. Of course, it is possible to perform various transformations without doing so.

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Claims (11)

[Claims] 1. In wheel landing gear assemblies for vertical takeoff and landing aircraft, suitable for mounting the wheel landing gear assembly on the underside of the vertical takeoff and landing aircraft; horizontal pipe, the wheel landing gear assembly is attached to the transverse tube to attach the wheel landing gear assembly to the vertical takeoff aircraft; when attached, a pair extending generally parallel to the longitudinal axis of the vertical takeoff aircraft. anteroposterior tube; a pivotable front leg attached to the front end of each of these longitudinal tubes; attached to the rear end of each of the longitudinal tubes and extending laterally outward from the rear end; cantilevered main landing gear struts and main landing gears attached to the laterally extending ends of each of these main landing gear struts; wheels and A wheel landing gear assembly containing. 2. Each of the longitudinal tubes is attached to a pivot bearing so that the tubes are tapered toward each other in front of the horizontal tube. and a spring assembly causes said pivotable front leg to be attached to said pivot bearing. The wheel landing gear assembly of claim 1, wherein the wheel landing gear assembly is adapted to be coupled to a wheel landing gear assembly. 3. An elastomer bearing allows each cantilevered main landing gear strut of the foreplane to be positioned adjacent to the transverse tube. The above The wheel landing gear assembly of claim 1, wherein the wheel landing gear assembly is adapted to be coupled to each longitudinal tube. 4. The stress of aircraft landing is determined by the deflection of the landing gear strut and the elasticity of the elastomeric bearing. 4. The wheel according to claim 3, wherein the absorption is effected by bending and twisting of the longitudinal tube. landing gear assembly. 5. In a quick-change nosewheel landing gear assembly for vertical takeoff and landing aircraft, a pair of planes extending generally parallel to the longitudinal axis of the vertical takeoff aircraft; A front-rear pipe and a pair of front-rear pipes, each of which is attached to the vertically detachable pipe. a front transverse pipe and a rear transverse pipe suitable for installation on the underside of an aircraft; a pivotable front leg attached to the front end of each longitudinal tube; attached to each of the longitudinal tubes, adjacent to the rear transverse tube and from each of the longitudinal tubes; a cantilevered main landing gear strut extending laterally outward; These main landing gear wheels are attached to the laterally extending ends of each main landing gear strut. A quick-replace nosewheel landing gear assembly containing. 6. An elastomeric bearing installed between the main landing gear strut and each of the longitudinal tubes. 6. The rapid change nosewheel landing gear assembly of claim 5, comprising: 7. Each of the longitudinal tubes interlocks in front of the front transverse tube for attaching the front leg. The design narrows at the tip and ends in a pivot bearing mounted on this front transverse pipe. 7. The quick-change nosewheel landing gear assembly of claim 6. 8. The front leg is provided with dual wheels attached to the pivot bearing by a spring assembly. 8. The quick-change nosewheel landing gear assembly of claim 7. 9. The stress of aircraft landing is calculated by the elasticity of the nose gear wheels and the main gear wheels, and the elasticity of the nose gear wheels. The elasticity of the spring assembly attached to the pivot bearing and the longitudinal tube and the lateral tube , the deflection of the main landing gear strut, the elasticity of the elastomeric bearing, and the front 9. The rapid replacement front wheel according to claim 8, wherein the absorption is achieved by twisting the tube in the rearward direction. formula landing gear assembly. 10. Quick installation suitable for replacing skid landing gear systems on helicopters. In addition to the replacement nosewheel landing gear assembly, a pair of front and rear wheels adapted to extend generally parallel to the longitudinal axis of said helicopter; A directional tube and a pair of forward and backward direction tubes attached to the lower side of the helicopter. Kid landing structure Equipped with a front side tube and a rear side piece suitable for mounting on the saddle, the front The anteroposterior tubes taper toward each other downwardly and forwardly of the anterior transverse tube, and end in a pivot bearing mounted on the tube, Additionally, a spring assembly provides a pivoting movable structure with dual wheels attached to said pivot bearing. a pair of front legs attached to each of said longitudinal tubes and adjacent to said rear transverse tubes; a cantilevered main landing gear strut extending laterally outwardly from the aft tube; an elastomeric bearing installed between each of the longitudinal tubes and the corresponding main landing gear strut; , a main landing gear wheel attached to a laterally extending end of the main landing gear strut; Quick-change nosewheel landing gear assembly with. 11. Helicopter Landing Stresses on the Rapid Replacement Nose Landing Gear Assembly the spring assembly and elastomeric bearing; and the deflection of the main landing gear strut; The rapid replacement according to claim 10, wherein the absorption is achieved by twisting the longitudinal tube. E nosewheel landing gear assembly.