CN204568052U - Ejection device, movable device and aircraft - Google Patents
Ejection device, movable device and aircraft Download PDFInfo
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- CN204568052U CN204568052U CN201520255406.4U CN201520255406U CN204568052U CN 204568052 U CN204568052 U CN 204568052U CN 201520255406 U CN201520255406 U CN 201520255406U CN 204568052 U CN204568052 U CN 204568052U
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Abstract
The utility model relates to ejection device, movable device and aircraft.According to an aspect of the present utility model, a kind of ejection device (10) for the movable device (MM) of aircraft (AC) is provided, described movable device (MM) comprises the special operations device (100) of main head and auxiliary described main head, the pushing tow assembly (UM) that described ejection device (10) comprises load-carrying element (20) and supported by described load-carrying element (20), described pushing tow assembly (UM) comprises top pushing element (40) and energy-accumulating element (50).When there is fracture in described special operations device (100), described top pushing element (40) is suitable for by the energy from described energy-accumulating element (50) by the breaking portion of described special operations device (100) from normal operation position (WP) pushing tow to deviation position (OP1, OP2).According to the utility model, effective emergency protection can be provided to the movable device of aircraft.
Description
Technical field
The utility model relates to ejection device, comprise the movable device of ejection device and comprise the aircraft of movable device, more specifically, relates to the ejection device that can provide the movable device for aircraft of effective emergency protection to the movable device of aircraft.
Background technology
In the aircraft of such as aircraft and so on, be provided with the multiple different movable part for realizing corresponding function.Such as, these movable parts are the various movable wings be arranged on wing, such as obtain at lower speeds compared with lift and better manipulation ability wing flap (wing flap can be divided into inner side wing flap and outside wing flap and can be divided into leading edge slat and trailing edge flap etc.), for control horizontal side attitude (gradient) of aircraft aileron and for increasing resistance to lower flap of air speed etc.
On the other hand, can the motion for cushioning movable part be set for movable part thus improve the damping arrangement of the stability of motion of movable part.Damping arrangement moves along with the motion of movable part, thus there is the possibility of fracture.Once damping arrangement ruptures, the breaking portion in damping arrangement likely clashes into the damage being difficult to the fixed sturcture keeped in repair for the fixed sturcture (skeleton structure of such as wing) and causing installing movable part of aircraft.In addition, breaking portion in damping arrangement may cause in addition after clashing into fixed sturcture and blocks situation thus cause movable part cannot continue motion and normally work to realize its expectation function, or, mutually interfere between two breaking portions in damping arrangement and cause and block situation thus also cause movable part cannot continue motion and normally work to realize its expectation function.
With reference to Fig. 1 (Fig. 1 is the block diagram of the first failure conditions of the damping arrangement for movable part illustrated according to correlation technique), occurs to rupture according to the collar 150A of the cylinder body side (left side in Fig. 1) of the damping arrangement 100A of correlation technique in FIG and clashed into the appropriate section of the fixed sturcture (such as rib 300A) to the wing for installing movement support structures 200A (movable part and then be arranged on movement support structures 200A to move integratedly with movement support structures 200A) and damping arrangement 100A.Thus, cause the damage of rib 300A (rib 300A is difficult to keep in repair usually), and, also likely cause to block situation thus cause movable part cannot continue motion and maybe cannot continue to move swimmingly (such as cannot or cannot swimmingly along the A direction rollback shown in Fig. 1).
With reference to Fig. 2 (Fig. 2 is the block diagram of the second failure conditions of the damping arrangement for movable part illustrated according to correlation technique), there is fracture according to the axostylus axostyle 120A of the damping arrangement 100A of correlation technique in fig. 2 or deviate from from cylinder body 110A, and the ends contact of the end of axostylus axostyle 120A and cylinder body 110A and interfering, causes thus and blocks situation and cause movement support structures 200A and then movable part cannot along the A direction rollback shown in Fig. 2.
Therefore, in the art, there is the demand to the technical scheme that above-mentioned situation occurs can be avoided.
Here, it should be pointed out that the technology contents provided in this part is intended to contribute to those skilled in the art to understanding of the present utility model, and not necessarily form prior art.
Utility model content
Total summary of the present utility model is provided in this part, instead of the complete scope of the utility model or the utility model institute characteristic comprehensively open.
An object of the present utility model is to provide a kind of ejection device that can provide effective emergency protection to the movable device of aircraft.
Another object of the present utility model is to provide a kind of with the ejection device of ingenious and simple principle of design structure.
The breaking portion that another object of the present utility model is to provide a kind of special operations device can avoided in movable device clashes into fixed sturcture and the ejection device that causes fixed sturcture to damage.
The breaking portion that another object of the present utility model is to provide a kind of special operations device can avoided in movable device causes and blocks situation thus cause movable device cannot continue to move and the ejection device of normal work.
Another object of the present utility model is to provide a kind of can being mounted to easily on fixed sturcture without the need to fixed sturcture and the very little ejection device of the change that makes a change or make the existing structure of movable device.
Another object of the present utility model is to provide a kind of ejection device being easy to manufacture and install.
Other object of the present utility model is that providing a kind of comprises the movable device of above-mentioned ejection device and a kind of aircraft comprising above-mentioned movable device.
One or more to achieve these goals, according to an aspect of the present utility model, a kind of ejection device of the movable device for aircraft is provided, described movable device comprises the special operations device of main head and auxiliary described main head, described ejection device comprises load-carrying element and the pushing tow assembly by described support member support, and described pushing tow assembly comprises top pushing element and energy-accumulating element.When fracture occurs described special operations device, described top pushing element is suitable for by the energy from described energy-accumulating element by the breaking portion of described special operations device from normal operation position pushing tow to deviation position.
According in ejection device of the present utility model, described energy-accumulating element is spring.
According in ejection device of the present utility model, described load-carrying element is support, pin-and-hole is formed in described support, described top pushing element is pin, described pin has pin head part and through the pin rod portion of described pin-and-hole, and described spring housing is in described pin rod portion and between described pin head part and described support.
According in ejection device of the present utility model, described load-carrying element is support, pin-and-hole is formed in described support, described top pushing element is pin, described pin has pin head part and pin rod portion, described pushing tow assembly also comprises flexible adjustment component, described flexible adjustment component has adjustment head and cylinder portion, described adjustment head is provided with the through hole passed for described pin rod portion, described spring is around described pin rod portion and between the adjustment head being sandwiched in described pin head part and being connected to the described flexible adjustment component in described pin-and-hole, and by regulating described flexible adjustment component relative to the position of described pin-and-hole, the bias force of described spring can be regulated thus can regulate described pin head part be resisted against the appropriate section of described special operations device against power.
According in ejection device of the present utility model, described cylinder portion is hollow cylinder to hold one end of described spring in described cylinder portion, the periphery in described cylinder portion is provided with outside thread, described pin-and-hole is provided with negative thread, described flexible adjustment component is suitable for being threaded with described pin-and-hole, regulates described flexible adjustment component relative to the position of described pin-and-hole thus.
According in ejection device of the present utility model, described ejection device also comprises transmission component, described transmission component is suitable for, by the Movement transmit of described special operations device extremely described ejection device, described ejection device being moved along with the motion of described special operations device.
According in ejection device of the present utility model, described transmission component is suitable for the appropriate section clamping described special operations device.
According in ejection device of the present utility model, keyhole is formed in described support, and described transmission component comprises guide gip, described guide gip passes and is connected to described keyhole, described guide gip have be suitable for clamping the appropriate section of described special operations device lead bolt stem.
According in ejection device of the present utility model, described guide gip comprises first pair of guide gip and second pair of guide gip, and described first pair of guide gip and described second pair of guide gip are clipped in the middle from outside by the appropriate section of described special operations device.
According in ejection device of the present utility model, axis hole is formed in described support, described shaft hole sleeve, in the installation shaft for installing described special operations device, makes the described ejection device when described special operations device rotates around described installation shaft also rotate around described installation shaft.
One or more to achieve these goals, according to another aspect of the present utility model, provide a kind of movable device for aircraft, comprising: main head; And special operations device, described special operations device moves along with the motion of described main head and realizes the expectation function of described main head for auxiliary described main head.Described movable device also comprises ejection device as above.
According in movable device of the present utility model, described main head is wing flap assembly.
According in movable device of the present utility model, described special operations device is damping arrangement.
According in movable device of the present utility model, described wing flap assembly comprises wing flap body and movement support structures, described wing flap body is fixedly mounted in described movement support structures to move integratedly with described movement support structures, described damping arrangement has near-end and far-end, described near-end is rotationally attached to the installation shaft at the fixed sturcture place attaching to described aircraft, described far-end is rotationally attached to the adapter shaft being arranged at described movement support structures, and described ejection device is arranged on the proximal lateral of described damping arrangement.
According in movable device of the present utility model, described near-end is rotationally attached to described installation shaft via near-end ball and cocket joint or near-end ball-bearing casing, and/or described far-end is rotationally attached to described adapter shaft via far-end ball and cocket joint or far-end ball-bearing casing.
According in movable device of the present utility model, described movable device also comprises and being arranged on below described damping arrangement to receive the receiving member of the described breaking portion fallen downwards.
One or more to achieve these goals, according to another aspect of the present utility model, provide a kind of aircraft.Described aircraft comprises movable device as above.
According to the utility model, construct the catapult-launching gear (ejection device) of the damping arrangement (special operations device) for movable device with ingenious and simple principle of design.Thus, once damping arrangement ruptures, before one of breaking portion in damping arrangement falls downwards, launched the deviation position to the normal operation position departing from damping arrangement in the horizontal direction by catapult-launching gear.Like this, that can avoid the shock of the breaking portion in damping arrangement aircraft causes for installing the fixed sturcture (rib of such as wing) of movable device the damage being difficult to the fixed sturcture keeped in repair.In addition, likely can cause after the shock of the breaking portion in damping arrangement fixed sturcture can also be avoided and block situation thus cause movable device cannot continue motion and normally work to realize its expectation function.In addition, can also to avoid between in damping arrangement two breaking portions mutually interfering and cause and block situation thus cause movable device cannot continue motion and normally work to realize its expectation function.
In addition, according to the utility model, catapult-launching gear for the damping arrangement of movable device can be mounted to aircraft fixed sturcture easily, and without the need to aircraft fixed sturcture (such as rib) and change that the existing structure of movable device and damping arrangement thereof is made a change or made very little.Therefore, the manufacture according to catapult-launching gear of the present utility model and installation easiness is improved further.
Accompanying drawing explanation
By the description referring to accompanying drawing, the feature and advantage of one or more embodiment of the present utility model will become easier to understand, in the accompanying drawings:
Fig. 1 is the block diagram of the first failure conditions of the damping arrangement for movable part illustrated according to correlation technique;
Fig. 2 is the block diagram of the second failure conditions of the damping arrangement for movable part illustrated according to correlation technique;
Fig. 3 is the block diagram of the catapult-launching gear illustrated according to the utility model illustrative embodiments;
Fig. 4 to Fig. 8 is the block diagram of the constituent elements of the catapult-launching gear illustrated according to the utility model illustrative embodiments respectively;
Fig. 9 is the schematic diagram of the installation for illustration of the catapult-launching gear according to the utility model illustrative embodiments;
Figure 10 is the elevation drawing that the catapult-launching gear according to the utility model illustrative embodiments being mounted to aircraft fixed sturcture is shown;
Figure 11 to Figure 15 is a series of figure of the working process of catapult-launching gear under damping arrangement first failure conditions illustrated according to the utility model illustrative embodiments;
Figure 16 to Figure 18 is a series of figure of the working process of catapult-launching gear under damping arrangement second failure conditions illustrated according to the utility model illustrative embodiments; And
Figure 19 illustrates the schematic diagram according to aircraft of the present utility model.
Detailed description of the invention
With reference to the accompanying drawings, by illustrative embodiments, the utility model is described in detail.Be only for purpose of explanation to following detailed description of the present utility model, and be never the restriction to the utility model and application or purposes.
First, with reference to Fig. 3 to Figure 10, the catapult-launching gear 10 according to the utility model illustrative embodiments is described.Wherein, Fig. 3 is the block diagram of the catapult-launching gear illustrated according to the utility model illustrative embodiments, Fig. 4 to Fig. 8 is the block diagram of the constituent elements of the catapult-launching gear illustrated according to the utility model illustrative embodiments respectively, Fig. 9 is the schematic diagram of the installation for illustration of the catapult-launching gear according to the utility model illustrative embodiments, and Figure 10 is the elevation drawing that the catapult-launching gear according to the utility model illustrative embodiments being mounted to aircraft fixed sturcture is shown.
As shown in the figure, catapult-launching gear 10 can comprise support 20, guide gip 30, pin 40 (corresponding to top pushing element), spring 50 (corresponding to energy-accumulating element) and screw element 60.Here, it is pointed out that catapult-launching gear 10 is used as according to ejection device of the present utility model.
Support 20 can be roughly microscler plate body, and its one end (right-hand member in Fig. 3 and also can be described as near-end) place is provided with axis hole 22 and its other end (left end in Fig. 3 and also can be described as far-end) place is provided with keyhole 24 and pin-and-hole 26.By axis hole 22 being enclosed within installation shaft 320 for installing damping arrangement 100 (see Fig. 9, and installation shaft 320 such as can be attached to the appropriate section of the rib 300 of wing regularly) on, support 20 rotatably can be mounted to rib 300 (being used as according to fixed sturcture of the present utility model).Here, it is pointed out that support 20 is used as according to load-carrying element of the present utility model.
Guide gip 30 can have head 32 and bar portion 34.In some instances, only outside thread (external thread part 35) can be set at the region place adjacent with head 32 in bar portion 34, and the distal end regions in bar portion 34 does not arrange outside thread (sliding supporting part 36).In other example, outside thread can be set in the whole length in bar portion 34.Guide gip 30 can be inserted through keyhole 24 and be threaded with keyhole 24 (keyhole 24 can be provided with negative thread), thus is attached to support 20 (see Fig. 3).But, the use of other the suitable mode that is fixedly connected with except being threaded can be conceived.
In the example shown in the series of figures, four guide gips 30 (correspondingly, being provided with 4 keyholes 24 in support 20) are provided with.As shown in Figure 10, be mounted to the installing condition of rib 300 at catapult-launching gear 10 under, damping arrangement 100 (being specially the jointing 160 for be connected the collar 150 and cylinder body adjacent with the collar 150 being arranged in cylinder body side of damping arrangement 100) is sandwiched in guide gip 30 (Figure 10 appreciable that to guide gip) and lower between guide gip 30 (Figure 10 does not see).Thus, along with damping arrangement 100 is rotated around installation shaft 320, catapult-launching gear 10 is also rotated around installation shaft 320 by the gearing of guide gip 30.Here, it is pointed out that guide gip 30 is used as according to transmission component of the present utility model.
Because transmission component is embodied as the guide gip 30 from the outside of damping arrangement 100 clamping damping arrangement 100, therefore can realize transmission component to the clamping of damping arrangement 100 realize the transmission of motion from damping arrangement 100 to catapult-launching gear 10 without the need to carrying out additional processing to damping arrangement 100.When damping arrangement 100 is outsourcing gauge members, this situation without the need to carrying out additional processing and change to existing structure is particularly advantageous.
Pin 40 can have head 42 (also referred to as abutting part) and bar portion 44.As shown in Figure 10, be mounted to the installing condition of rib 300 at catapult-launching gear 10 under, head 42 is resisted against jointing 160.
Spring 50 can helically form of springs.But, the use of other suitable types of springs can be conceived.
Screw element 60 (also referred to as flexible adjustment component) can have head 62 and cylinder portion 64.Head 62 can in hexagon plate body so that use particular tool to carry out rotary screwing thread part 60.Head 62 can be provided with central through hole and pass with the bar portion 44 of supply and marketing 40.Cylinder portion 64 can for hollow cylinder to hold one end of spring 50 in cylinder portion 64.The periphery in cylinder portion 64 can be provided with outside thread, and screw element 60 can be threaded with pin-and-hole 26 (pin-and-hole 26 can be provided with negative thread) thus.
As shown in Figure 10, be mounted to the installing condition of rib 300 at catapult-launching gear 10 under, spring 50 around pin 40 bar portion 44 and between the head 42 being sandwiched in pin 40 and the head 62 having screwed to the screw element 60 in pin-and-hole 26.By rotary screwing thread part 60, can the compression degree (i.e. prestrain degree) of regulating spring 50 easily.In some instances, (each) spring 50 can be adjusted to the elastic force that can apply (approximately) 80N.Here, it is pointed out that pin 40, spring 50 and screw element 60 can be formed and launch assembly or pushing tow assembly UM according to of the present utility model.
In the example shown in the series of figures, be provided with two and launch assembly (i.e. two groups of pins 40, spring 50 and screw elements 60), and two launch assembly on the horizontal direction (vertical direction in Fig. 3) of catapult-launching gear 10 upper to guide gip 30 and lower to guide gip 30 between.
In the example shown in the series of figures, catapult-launching gear 10 is arranged on the cylinder body side of damping arrangement 100.Like this, owing to usually having wider space near the cylinder body side of damping arrangement 100 and being suitable for being clamped by guide gip and being launched assembly launching due to the jointing 160 being positioned at cylinder body side of damping arrangement 100, therefore this set is particularly advantageous.
Referring to Figure 11, the movable device MM of application according to the catapult-launching gear 10 of the utility model illustrative embodiments is described.
Such as, movable device MM is arranged on the rib 300 of wing movably.In some instances, movable device MM can comprise wing flap assembly (not shown), such as inner side wing flap (IBF).Wing flap assembly comprises wing flap body and movement support structures (portable bar) 200, to move integratedly with movement support structures 200 on the upper surface 210 that wing flap body can be fixedly mounted in movement support structures 200.Movement support structures 200 can with axle portion (Figure 11 is not shown, but can see the axle portion 220A shown in Fig. 1 corresponding with it) for centre of gration rotates under the driving of flap actuator (not shown) together with wing flap body (i.e. wing flap assembly).In addition, the far-end of movement support structures 200 can also be provided with the adapter shaft 230 for being connected with damping arrangement 100.When (for Figure 11) rotates movement support structures 200 in the counterclockwise direction, wing flap body is towards wing-body rollback, and when (for Figure 11) rotates movement support structures 200 along clockwise direction, wing flap body stretches towards the outside of wing-body.
In order to cushion the motion of movable device MM thus improve the stability of motion of movable device MM, damping arrangement 100 can be set for movable device.In the example shown in the series of figures, damping arrangement 100 can comprise: cylinder body 110 (such as double-cylinder structure); To be inserted in cylinder body 110 thus the axostylus axostyle 120 that can slide relative to cylinder body 110; Be arranged in the cylinder body side (left side of Figure 11) of damping arrangement 100, for being enclosed within the proximal collar 150 in the installation shaft 320 of rib 300; Adjacent with the collar 150 jointing 160 for being connected the collar 150 and cylinder body 110 (in some instances, jointing 160 can be formed as having a pair flat condition opposed surface being suitable for being clamped by guide gip 30 and have be suitable for by the head 42 of pin 40 against flat condition surface, further, jointing 160 corresponds to according to appropriate section of the present invention); And be arranged in damping arrangement 100 axostylus axostyle side (right side of Figure 11), for being enclosed within the distal collar 170 on the adapter shaft 230 of movement support structures 200.Here, it is pointed out that damping arrangement 100 is used as according to special operations device of the present utility model, and wing flap assembly is used as according to main head of the present utility model.Main head is that aircraft realizes the requisite device of corresponding expectation function, and special operations device is used for assisting main head reliably to realize its expectation function, but main head still can realize completely when such as lacking some performance (such as stability of motion) or substantially realize its expectation function when special operations failure of apparatus.
When movement support structures 200 rotates for centre of gration with axle portion, damping arrangement 100 servo-actuatedly with installation shaft 320 for centre of gration rotate, meanwhile, slide in cylinder body 110 in damping arrangement 100 central shaft rod 120 and make damping arrangement 100 that fore and aft motion occur.Thus, damping arrangement 100 plays the effect of the motion of buffering movement support structures 200 and then wing flap body.Such as, damping arrangement 100 can adopt the damping form that hydraulic damping, air damping and mechanical damping (such as mechanical spring) etc. are suitable.
In preferred example, proximal collar 150 and/or distal collar 170 are provided with ball and cocket joint (the near-end ball and cocket joint 180 at the place of proximal collar 150 shown in Fig. 9).Owing to adopting ball and cocket joint; except allowing damping arrangement 100 except following normal operation position is rotated; also allow damping arrangement 100 in a break situation easily by the deviation position that catapult-launching gear 10 pushing tow is extremely following, guarantee that catapult-launching gear 10 can realize the defencive function of its expection thus.
In preferred example, in movable device MM, be provided with receiving member 400.Receiving member can in channel form to receive the breaking portion fallen of the damping arrangement 100 of the fracture that meets accident downwards.When breaking portion is received on receiving member 400, the damping arrangement 100 having occurred to rupture can not interfere the proper motion (especially rollback motion) of movable device MM, although thus disappearance damping movable device MM still can work on.
The exemplary installation process being mounted to rib 300 according to the catapult-launching gear 10 of the utility model illustrative embodiments is described below.
With reference to Fig. 9 and Figure 10, by in the installation shaft 320 (in some instances, installation shaft 320 can be attached to rib 300 regularly) of the shaft hole sleeve of the catapult-launching gear 10 of (see Fig. 3) under being in assembled state in the appropriate section of rib 300 being arranged on wing.Then, in turn the proximal collar 150 of lining 330, damping arrangement 100 and packing ring 340 are enclosed within installation shaft 320.Then, clamp nut 350 is screwed on the screw tip of installation shaft 320.
Under the installing condition of catapult-launching gear 10, lining 330 is by catapult-launching gear 10 (being specially the near-end being provided with axis hole 22 of support 20) and damping arrangement 100 (being specially proximal collar 150) spaced apart preset distance.Meanwhile, under the installing condition of catapult-launching gear 10, the jointing 160 of damping arrangement 100 is sandwiched between guide gip 30, and the head 42 of pin 40 is resisted against jointing 160 under the effect of the bias force of spring 50.
Referring to Figure 11 to Figure 15, the working process of catapult-launching gear 10 under damping arrangement first failure conditions (Figure 11 to Figure 15 is a series of figure of the working process of catapult-launching gear under damping arrangement first failure conditions illustrated according to the utility model illustrative embodiments) according to the utility model illustrative embodiments is described.
In fig. 11, movement support structures 200 is rotated in a clockwise direction and wing flap body is outwards stretched.Thus, damping arrangement 100 is also rotated in a clockwise direction and extends along longitudinally simultaneously.Now, catapult-launching gear 10 also rotates along with the rotation of damping arrangement 100.
In fig. 12, movement support structures 200 continues to be rotated in a clockwise direction and damping arrangement 100 continues to extend along longitudinally, and the proximal collar 150 of damping arrangement 100 ruptures at this moment.
In fig. 13, the damping arrangement 100 having occurred to rupture is clamped provisionally by guide gip 30 and can not fall downwards immediately and clash into the appropriate section be positioned at below damping arrangement 100 of rib 300, meanwhile, in advance by under the effect of the bias force of the spring 50 of suitable prestrain, there is the jointing 160 of the damping arrangement 100 ruptured in the head 42 of pin 40 in the horizontal direction () pushing tow in Figure 13 in downward direction, thus the right part (for Figure 13) that the damping arrangement 100 ruptured occurs is launched the deviation position OP1 (see Figure 15) to the normal operation position WP departing from damping arrangement 100 (see Figure 15) in the horizontal direction.Thus, the breaking portion fallen of damping arrangement 100 is made to depart from the appropriate section below the normal operation position being positioned at damping arrangement 100 of rib 300 in the horizontal direction thus this appropriate section can not be clashed into downwards.Here, it is to be noted, deviation position can refer to following position: the breaking portion of damping arrangement can not clash into being positioned at the appropriate section below damping arrangement 100 but falling safely on receiving member 400 of rib 300 downwards downwards when falling in this position, and one of them breaking portion falls downwards in this position and guarantees that two breaking portions to fall safely to receiving member 400 thus avoid the fracture end in contact of two breaking portions and interfere downwards when two breaking portions fall downwards.
In figures 14 and 15, with different viewing angle, being fallen safely on receiving member 400 by the breaking portion launched to deviation position OP1 of damping arrangement 100 is shown downwards.
Referring to Figure 16 to Figure 18, the working process of catapult-launching gear 10 under damping arrangement second failure conditions (Figure 16 to Figure 18 is a series of figure of the working process of catapult-launching gear under damping arrangement second failure conditions illustrated according to the utility model illustrative embodiments) according to the utility model illustrative embodiments is described.
In figure 16, the axostylus axostyle 120 being stretched to damping arrangement 100 to a certain degree ruptures at the BP place, position near cylinder body 110.
In fig. 17, the damping arrangement 100 having occurred to rupture is clamped provisionally by guide gip 30 and can not fall downwards immediately, meanwhile, in advance by under the effect of the bias force of the spring 50 of suitable prestrain, there is the jointing 160 of the damping arrangement 100 ruptured in the head 42 of pin 40 in the horizontal direction () pushing tow in Figure 17 in downward direction, thus the left part (for Figure 17) that the damping arrangement 100 ruptured occurs is launched the deviation position OP2 (see Figure 17) to the normal operation position WP departing from damping arrangement 100 (see Figure 17) in the horizontal direction.Thus, the left side breaking portion of damping arrangement 100 is fallen at deviation position OP2 downwards, make the right side breaking portion (for Figure 17) of damping arrangement 100 fall at normal operation position WP simultaneously downwards.Like this, because two breaking portions fall downwards with mutually departing from the horizontal direction, therefore the fracture end of two breaking portions can not contact and interfere, thus can not cause and block situation and cause movement support structures 200 and then whole movable device MM cannot carry out proper motion (especially rollback motion).
In figure 18, left side breaking portion and right side breaking portion fall on receiving member 400 downwards with mutually departing from the horizontal direction, simultaneously movement support structures 200 together with wing flap body completely rollback to retracted position.
According to the utility model illustrative embodiments, construct the catapult-launching gear of the damping arrangement for movable device with ingenious and simple principle of design.Thus, once damping arrangement ruptures, before one of breaking portion in damping arrangement falls downwards, launched the deviation position to the normal operation position departing from damping arrangement in the horizontal direction by catapult-launching gear.Like this, that can avoid the shock of the breaking portion in damping arrangement aircraft causes for installing the fixed sturcture (rib of such as wing) of movable device the damage being difficult to the fixed sturcture keeped in repair.In addition, likely can cause after the shock of the breaking portion in damping arrangement fixed sturcture can also be avoided and block situation thus cause movable device cannot continue motion and normally work to realize its expectation function.In addition, can also to avoid between in damping arrangement two breaking portions mutually interfering and cause and block situation thus cause movable device cannot continue motion and normally work to realize its expectation function.
In addition, according to the utility model illustrative embodiments, catapult-launching gear for the damping arrangement of movable device can be mounted to aircraft fixed sturcture easily, and without the need to aircraft fixed sturcture (such as rib) and change that the existing structure of movable device and damping arrangement thereof is made a change or made very little.Therefore, the manufacture according to the catapult-launching gear of the utility model illustrative embodiments and installation easiness is improved further.
Can allow multiple different modification according to catapult-launching gear of the present utility model, these modification can obtain the effect substantially identical with the effect of the above-mentioned catapult-launching gear according to the utility model illustrative embodiments.
In above-mentioned illustrative embodiments, four guide gips are set and two launch assembly.But can conceive, guide gip can change with the quantity of launching assembly (fabricate block of pin, spring and screw element).
In above-mentioned illustrative embodiments, transmission component is embodied as guide gip.But, other suitable form of transmission component can be conceived, such as from upper and lower both sides, the appropriate section of damping arrangement is clamped in middle train wheel bridge and lower plate, again such as rotatably and the guide gip that can be inserted into axially slidably in the slide opening at the appropriate section place being arranged on damping arrangement.
In above-mentioned illustrative embodiments, launch assembly/pushing tow assembly and be embodied as mechanical coil spring assembly.But, other suitable form launching assembly can be conceived, such as Pneumatic assembly and can automatically actuated pyrotechnics pushing tow assembly when damping arrangement ruptures.
In above-mentioned illustrative embodiments, catapult-launching gear moves along with the motion of damping arrangement.But, it is contemplated that launching assembly also can be static relative to damping arrangement.Such as, when launching assembly and adopting pyrotechnics pushing tow assembly, launch assembly to move with the motion of damping arrangement, if the position when fracture occurs damping arrangement no matter at that time residing for damping arrangement how to launch assembly all can effectively by breaking portion pushing tow to deviation position.
In above-mentioned illustrative embodiments, load-carrying element is embodied as support.But, other suitable form of load-carrying element can be conceived, such as, directly from the static load-carrying element that fixed sturcture extends.
In above-mentioned illustrative embodiments, special operations device is embodied as damping arrangement.But, other suitable form of special operations device can be conceived, such as, for reliably realizing other special operations device also moved along with the motion of wing flap assembly of its expectation function from other side auxiliary flap assembly.
In above-mentioned illustrative embodiments, main head example is wing flap assembly.But, other suitable form of main head can be conceived, such as, other head (such as aileron assembly, flap assembly, elevating rudder assembly and rudder unit) on aircraft.
In the utility model, be also provided for the movable device comprising ejection device of aircraft AC.
In the utility model, also provide the aircraft AC comprising movable device (special in Figure 19, wherein Figure 19 illustrates the schematic diagram according to aircraft of the present utility model).
In present specification, the use of directional terminology "up" and "down" etc. only for the object being convenient to describe, and should not be considered as being restrictive.
In this manual, whenever mentioning " illustrative embodiments ", " some examples ", " other example ", " preferred example " and " graphic example " etc., mean that concrete feature, structure or the feature described for this embodiment/example is included at least one embodiment/example of the present utility model.The different in this manual local appearance of these words differs to establish a capital and refers to same embodiment/example.In addition, when describing concrete feature, structure or feature for arbitrary embodiment/example, will be understood that those skilled in the art also can realize this feature, structure or feature in other embodiment/example in all described embodiment/examples.
Although be described the utility model with reference to illustrative embodiments, should be appreciated that the utility model is not limited in literary composition the detailed description of the invention/example described in detail and illustrate.When not departing from claims limited range, those skilled in the art can make various change to illustrative embodiments.
Claims (17)
1. the ejection device (10) of the movable device for aircraft (AC) (MM), described movable device (MM) comprises the special operations device (100) of main head and auxiliary described main head, the pushing tow assembly (UM) that described ejection device (10) comprises load-carrying element (20) and supported by described load-carrying element (20), described pushing tow assembly (UM) comprises top pushing element (40) and energy-accumulating element (50)
It is characterized in that, when there is fracture in described special operations device (100), described top pushing element (40) is suitable for by the energy from described energy-accumulating element (50) by the breaking portion of described special operations device (100) from normal operation position (WP) pushing tow to deviation position (OP1, OP2).
2. ejection device according to claim 1 (10), wherein, described energy-accumulating element (50) is spring (50).
3. ejection device according to claim 2 (10), wherein
Described load-carrying element (20) is support (20), is formed with pin-and-hole (26) in described support (20),
Described top pushing element (40) is pin (40), and described pin (40) has pin head part (42) and the pin rod portion (44) through described pin-and-hole (26), and
Described spring (50) is enclosed within described pin rod portion (44) and goes up and be positioned between described pin head part (42) and described support (20).
4. ejection device according to claim 2 (10), wherein
Described load-carrying element (20) is support (20), is formed with pin-and-hole (26) in described support (20),
Described top pushing element (40) is pin (40), and described pin (40) has pin head part (42) and pin rod portion (44),
Described pushing tow assembly (UM) also comprises flexible adjustment component (60), described flexible adjustment component (60) has adjustment head (62) and cylinder portion (64), described adjustment head (62) is provided with the through hole passed for described pin rod portion (44)
Described spring (50) is around described pin rod portion (44) and between the adjustment head (62) being sandwiched in described pin head part (42) and being connected to the described flexible adjustment component (60) in described pin-and-hole (26), and
By regulating described flexible adjustment component (60) relative to the position of described pin-and-hole (26), the bias force of described spring (50) can be regulated thus can regulate described pin head part (42) be resisted against the appropriate section (160) of described special operations device (100) against power.
5. ejection device according to claim 4 (10), wherein, described cylinder portion (64) is for hollow cylinder so that in the middle one end holding described spring (50) of described cylinder portion (64), the periphery of described cylinder portion (64) is provided with outside thread, described pin-and-hole (26) is provided with negative thread, described flexible adjustment component (60) is suitable for being threaded with described pin-and-hole (26), regulates described flexible adjustment component (60) relative to the position of described pin-and-hole (26) thus.
6. the ejection device (10) according to any one of claim 3 to 5, wherein, described ejection device (10) also comprises transmission component (30), described transmission component (30) is suitable for, by the Movement transmit of described special operations device (100) extremely described ejection device (10), described ejection device (10) being moved along with the motion of described special operations device (100).
7. ejection device according to claim 6 (10), wherein, described transmission component (30) is suitable for the appropriate section (160) clamping described special operations device (100).
8. ejection device according to claim 7 (10), wherein
Keyhole (24) is formed in described support (20), and
Described transmission component (30) comprises guide gip (30), described guide gip (30) passes and is connected to described keyhole (24), described guide gip (30) have be suitable for clamping the appropriate section (160) of described special operations device (100) lead bolt stem (34).
9. ejection device according to claim 8 (10), wherein, described guide gip (30) comprises first pair of guide gip (30) and second pair of guide gip (30), and described first pair of guide gip (30) and described second pair of guide gip (30) are clipped in the middle from outside by the appropriate section (160) of described special operations device (100).
10. the ejection device (10) according to any one of claim 3 to 5, wherein, axis hole (22) is formed in described support (20), described axis hole (22) is enclosed within the installation shaft (320) for installing described special operations device (100), and the described ejection device (10) when described special operations device (100) rotates around described installation shaft (320) is also rotated around described installation shaft (320).
11. 1 kinds of movable devices for aircraft (AC) (MM), comprising:
Main head; And
Special operations device (100), described special operations device (100) is moved along with the motion of described main head and is realized the expectation function of described main head for auxiliary described main head,
It is characterized in that, described movable device (MM) also comprises the ejection device (10) according to any one of claim 1 to 10.
12. movable devices according to claim 11 (MM), wherein, described main head is wing flap assembly.
13. movable devices according to claim 12 (MM), wherein, described special operations device (100) is damping arrangement (100).
14. movable devices according to claim 13 (MM), wherein
Described wing flap assembly comprises wing flap body and movement support structures (200), and it is upper to move integratedly with described movement support structures (200) that described wing flap body is fixedly mounted in described movement support structures (200),
Described damping arrangement (100) has near-end and far-end, described near-end is rotationally attached to the installation shaft (320) at fixed sturcture (300) place attaching to described aircraft, described far-end is rotationally attached to the adapter shaft (230) being arranged at described movement support structures (200), and
Described ejection device (10) is arranged on the proximal lateral of described damping arrangement (100).
15. movable devices according to claim 14 (MM), wherein, described near-end is rotationally attached to described installation shaft (320) via near-end ball and cocket joint (180) or near-end ball-bearing casing, and/or described far-end is rotationally attached to described adapter shaft (230) via far-end ball and cocket joint or far-end ball-bearing casing.
16. movable devices according to claim 15 (MM), wherein, described movable device (MM) also comprises and is arranged on described damping arrangement (100) below to receive the receiving member (400) of described breaking portion fallen downwards.
17. 1 kinds of aircraft (AC), is characterized in that, described aircraft (AC) comprises the movable device (MM) according to any one of claim 11 to 16.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520255406.4U CN204568052U (en) | 2015-04-24 | 2015-04-24 | Ejection device, movable device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520255406.4U CN204568052U (en) | 2015-04-24 | 2015-04-24 | Ejection device, movable device and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204568052U true CN204568052U (en) | 2015-08-19 |
Family
ID=53860726
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520255406.4U Withdrawn - After Issue CN204568052U (en) | 2015-04-24 | 2015-04-24 | Ejection device, movable device and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204568052U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143876A (en) * | 2015-04-24 | 2016-11-23 | 空客(北京)工程技术中心有限公司 | Thrustor, movable device and aircraft |
-
2015
- 2015-04-24 CN CN201520255406.4U patent/CN204568052U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143876A (en) * | 2015-04-24 | 2016-11-23 | 空客(北京)工程技术中心有限公司 | Thrustor, movable device and aircraft |
| CN106143876B (en) * | 2015-04-24 | 2023-11-24 | 空客(北京)工程技术中心有限公司 | Pushing device, moving mechanism and aircraft |
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