Patent ID: 12188264

DETAILED DESCRIPTION

The illustrative embodiments recognize and take into account one or more different considerations. For example, the illustrative embodiments recognize and take into account a typical wing lock and deployment system for an air launched vehicle requires three separate mechanisms and three separate commands from a control system for unlocking deployable wings from a locked condition, deploying the wings from a stored position to a deployed position, and relocking the wings in the deployed position.

The illustrative embodiments recognize and take into account that requiring three separate mechanisms and three separate command signals to unlock, deploy, and relock deployable wings of an air launched vehicle is overly complicated, costly, and requires specific timing of the three separate commands.

Thus, the illustrated embodiments provide a wing lock and deployment apparatus that allows for a single command to unlock deployable wings of an air launched vehicle, deploy the wings to a deployed position, and relock the wings in the deployed position. The illustrated embodiments eliminate the needs for three separate mechanisms with their own actuators and mechanism inputs and instead accomplish all three tasks with one single linear actuation event.

The illustrated embodiments provide a wing lock and deployment apparatus and system which only receives one input and accomplishes all three tasks in order, reliably and inexpensively.

With reference now to the figures and, in particular, with reference toFIG.1, an illustration of a glide kit of an air launched vehicle is depicted in accordance with an illustrative embodiment. Glide kit100has housing102, deployable wing104and deployable wing106, and wing lock and deployment apparatus108. Housing102acts a base or platform for mounting the components of glide kit100thereon. Housing102also provides an attachment point of glide kit100to structure of an air launched vehicle. The air launched vehicle, complete with attached glide kit100, may be carried or transported by a host aircraft (not shown) until deployed from the host aircraft.

Deployable wing104is pivotally mounted on housing102. Deployable wing106is pivotally mounted on housing102. Deployable wing104and deployable wing106are illustrated in a stored position inFIG.1. Deployable wing104and deployable wing106may pivot with respect to housing102from the stored position (FIG.1) to a deployed position (FIG.3). Wing lock and deployment apparatus108is mounted to housing102. In the stored position, while the air launched vehicle is transported by the host aircraft, wing lock and deployment apparatus108securely locks deployable wing104and deployable wing106in the stored position. To maintain safety of flight certifications, the deployable wings must not be unlocked and deployed until the air launched vehicle has separated from the host aircraft.

After launching the air launched vehicle with glide kit100attached from the host aircraft, a single command received by wing lock and deployment apparatus108initiates a single linear actuation event which causes wing lock and deployment apparatus108to sequentially unlock deployable wing104and unlock deployable wing106from the stored position, deploy deployable wing104and deployable wing106, and lock the deployable wings in the deployed position. Wing lock and deployment apparatus108accomplishes the three operations of unlocking, deploying, and locking the deployable wings in a sequential manner with a single command. In other words, deploying the wings occurs after the wings are unlocked and locking the wings in the deployed position occurs after the wings are deployed. A single command received by wing lock and deployment apparatus108initiates the three sequentially ordered operations. Wing lock and deployment apparatus108is capable of accomplishing the three sequentially ordered operations upon receiving a single command.

With reference next toFIGS.2-4, illustrations of a wing lock and deployment apparatus of a glide kit for an air launched vehicle are depicted in accordance with illustrative examples.

In these illustrated examples, wing lock and deployment apparatus108has motor202, ball nut204, driver206, lock rod208, spring210, and shoe clip212.

Motor202is mounted to housing102. Motor202provides rotational motion which wing lock and deployment apparatus108converts to linear motion applied to driver206. As depicted, motor202rotates a ball screw (described below) which ball nut204which, in turn, engages driver206and provides linear movement of driver206. Linear movement of driver206is not limited to a motor and ball nut/ball screw setup. Those skilled in the art recognize that linear motion could be imparted to driver206by other means including, but not limited to, for example, a linear actuator. As a result, driver206has a resting state before linear motion is imparted to driver206and a moving state as linear motion is imparted to driver206.

As depicted, ball nut204is threadably engaged with ball screw302(FIG.3) and ball screw302is mechanically engaged with motor202. Motor202rotates ball screw302. As ball screw302rotates, ball nut204moves in direction214along ball screw302. Ball screw302passes through driver206without engaging driver206. As ball nut204moves in direction214, ball nut204engages driver206and imparts linear motion on driver206in direction214. When ball nut204engages driver206and imparts linear motion on driver206, driver206is in a moving state.

Lock rod208extends from driver206to shoe clip212. Shoe clip212is mounted to end304of lock rod208. Movement of lock rod208relative to driver206is fixed. Lock rod208may be integrally formed with driver206or connected to driver206, for example, by weld, casting, or billet machining. As a result, motion in driver206produces motion in lock rod208. When driver206moves in direction214, lock rod208moves in direction214. As depicted, pin216passing horizontally through lock rod208and pin218passing horizontally through lock rod208constrain movement of lock rod208relative to driver206in direction214and direction215. Direction215is parallel with direction214. Spring210surrounds lock rod208and abuts pin218.

In the stored position, as depicted inFIGS.2and4-6, lock rod208passes through, without engagement with, wing shoe224and wing shoe226. Wing shoe224is connected to deployable wing104. Wing shoe226is connected to deployable wing106. A toothed edge of wing shoe224engages a mating toothed edge of wing shoe226when deployable wing104and deployable106are in the stored position as depicted inFIGS.2and4-6. The engagement of the toothed edges of wing shoe224and wing shoe226prevent movement of the deployable wings relative to each other as the air launched vehicle glide kit100is attached to and transported by the host aircraft. While in the stored position, driver206is in a resting state.

Spring210provides bias220. As depicted, spring210surrounds lock rod208and abuts pin218and abuts wing shoe224and wing shoe226such that bias220urges driver206in direction215. The urged movement of driver206provided by bias220is not limited to the pins and spring setup depicted. Those skilled in the art recognize that bias may be imparted to driver206by other means including, but not limited to, for example, a biased slider joint.

As driver206is urged in direction215, shoe clip mounted on end304of lock rod208is also urged in direction215which results in shoe clip212simultaneously engaging wing shoe224and wing shoe226. When shoe clip212mounted to end304of lock rod208simultaneously engages wing shoe224and wing shoe226, shoe clip212locks deployable wing104and deployable wing106in the stored position. Bias220of spring210keeps the wings locked in the stored position until driver206moves in direction214and disengages shoe clip212from engagement with wing shoe224and wing shoe226. Once shoe clip212disengages from wing shoe224and wing shoe226, the deployable wings are no longer locked in the stored position and further movement of driver206in direction214results in deployable wing104and deployable wing106rotating to the deployed position (described below).

With reference next toFIGS.5-6, illustrations of a wing lock and deployment apparatus of a glide kit for an air launched vehicle where deployable wings of the glide kit are shown in shadow are depicted in accordance with an illustrative example.

In these illustrated examples, wing lock and deployment apparatus108further includes linkage504and linkage506. Linkage504is rod-shaped and includes end508opposite end510. Linkage506is rod-shaped and includes end512opposite end514. End510of linkage504is pivotally connected to deployable wing104at axis520. Axis520is generally perpendicular to direction214and direction215. End514of linkage506is pivotally connected to deployable wing106at axis522. Axis522is generally perpendicular to direction214and direction215.

End508of linkage504and end512of linkage506are both ball-shaped. End508and end512are pivotable with respect to driver206. End512is slidable within slot530. Slot530is formed in driver206. Slot530is cylindrical shaped. Thus end512can pivot within slot530and slide through the length of slot530from end532of slot530to end534of slot530. Although not visible, another slot formed on the opposite side of driver206engages end508of linkage504in an identical manner. Slot530and the other slot formed on the opposite side of the driver are generally parallel. Pin524engages driver206. Pin524extends through driver206and into slot530. Pin524prevents end512of linkage506from exiting end534of slot530formed in driver206. Pin525is similar to pin524and provides the same function with regard to the slot formed on the opposite side of driver206.

When in the stored position and shoe clip212simultaneously engaged with wing shoe224and wing shoe226such that the deployable wings are locked in the stored position, end512of linkage506is positioned near end534of slot530. End508of linkage504is correspondingly positioned in the same manner in the slot on the opposite side of driver206.

Upon receiving a single command to unlock and deploy the deployable wings, wing lock and deployment apparatus108imparts linear movement to driver206. Driver206linearly moves in direction214against bias220of spring210. As driver206moves in direction214, lock rod208pushes shoe clip212out of engagement with wing shoe224and wing shoe226thus unlocking the deployable wings. Simultaneously, end512slides through slot530from end534to end532. End508moves in an identical manner through its respective slot in driver206. End512and end508slide through the length of their respective slots until they reach the end of their respective slots resulting in shoe clip212disengaging from wing shoe224and wing shoe226. The deployable wings are effectively “unlocked” and ready for deployment. While end512and end508are moving through the length of their respective slots, linkage504and linkage506do not move with respect to housing102or the deployable wings.

Once the deployable wings are unlocked, as driver206moves further in direction214, the movement of driver206pushes linkage504and linkage506. The movement of linkage504and linkage506combined with the pivotal engagement of linkage504with driver206and deployable wing104as well as the pivotal engagement of linkage506with driver206and deployable wing106forces the deployable wings to rotate about axes520and522to deploy to the deployed position depicted inFIG.3.

A stop on each deployable wing104and deployable wing106prevents rotation of the deployable wings past the deployed position. Once the wings are in the deployed position, their respective angles with respect to housing102and the wind resistance each are inherently experiencing during use locks the deployable wings in the deployed position. Further, the geometry of the linkages, once the deployable wings are in the deployed position, prevents the driver from movement in direction215thus locking the deployable wings in the deployed position.

With reference next toFIGS.7-8, an illustration of components of a wing lock and deployment apparatus is depicted in accordance with an illustrative example. In the illustrative examples, the same reference numeral may be used in more than one figure. This reuse of a reference numeral in different figures represents the same element in the different figures.

Driver702further includes slot704and slot706. Linkage708is pivotally attached to driver702with fastener712. Linkage710is pivotally attached to driver702with fastener714. The operation of the linkages sliding through respective slots in the driver operates in a similar manner. However, here, fastener712also slides through the length of slot706and fastener714slides through the length of slot704at the same time as the linkages slide through the length of their respective slots.

With reference next toFIG.9, an illustration of a flowchart of a process900for unlocking and deploying wings of an air launched vehicle is depicted in accordance with an illustrative embodiment. The method depicted inFIG.9may be used in conjunction with the wing lock and deployment apparatus depicted inFIGS.1-8.

The process begins by providing a wing lock and deployment apparatus for attachment to an air launched vehicle (operation902). The wing lock and deployment apparatus may include features and structure as depicted inFIGS.1-8. The process receives a single command to initiate linear movement of a driver of the wing lock and deployment apparatus from a resting state to a moving state (operation904). When the driver is in the resting state, a bias on the driver forces a shoe clip of the driver into engagement with deployable wings to put the wing lock and deployment apparatus in a locked position. When the driver is in the moving state, the driver overcomes the bias to disengage the shoe clip from engagement with deployable wings. Further while the driver in in the moving state, rod-shaped linkages that are pivotally connected to the deployable wings move from a first end of a slot in the driver through a length of the slot to a second end of the slot in the driver as the shoe clip of the driver disengages from the deployable wings. When the linkages are positioned in the second end of the slot and the shoe clip is disengaged from the deployable wings, the linkages force rotation of the deployable wings from a stored position to a deployed position. At operation906, as a result of the linear movement of the driver, the process sequentially unlocks the deployable wings from a stored position, deploys the deployable wings from the stored position, and locks the deployable wings in a deployed position.

In some alternative implementations of an illustrative example, the function or functions noted in the blocks may occur out of the order noted in the figures. For example, in some cases, two blocks shown in succession may be performed substantially concurrently, or the blocks may sometimes be performed in the reverse order, depending upon the functionality involved. Also, other blocks may be added in addition to the illustrated blocks in a flowchart or block diagram.

The illustrative embodiments of the disclosure may be further described in the context of aircraft manufacturing and service method1000as shown inFIG.10and aircraft1100as shown inFIG.11. Turning first toFIG.10, an illustration of a block diagram of an aircraft manufacturing and service method is depicted in accordance with an illustrative embodiment. During pre-production, aircraft manufacturing and service method1000may include specification and design1002of aircraft1100inFIG.11and material procurement1004. Aircraft1100inFIG.11may be an air launched vehicle or a host aircraft as previously described.

During production, component and subassembly manufacturing1006and system integration1008of aircraft1100inFIG.11takes place. Thereafter, aircraft1100inFIG.11may go through certification and delivery1010in order to be placed in service1012. While in service1012by a customer, aircraft1100inFIG.11is scheduled for routine maintenance and service1014, which may include modification, reconfiguration, refurbishment, and other maintenance or service.

Each of the processes of aircraft manufacturing and service method1000may be performed or carried out by a system integrator, a third party, an operator, or some combination thereof. In these examples, the operator may be a customer. For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and major-system subcontractors; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, a leasing company, a military entity, a service organization, and so on.

With reference now toFIG.11, an illustration of a block diagram of an aircraft is depicted in which an illustrative embodiment may be implemented. In this example, aircraft1100is produced by aircraft manufacturing and service method1000inFIG.10and may include airframe1102with plurality of systems1104and interior1106. Examples of systems1104include one or more of propulsion system1108, electrical system1110, hydraulic system1112, and environmental system1114. Any number of other systems may be included. Although an aerospace example is shown, different illustrative embodiments may be applied to other industries, such as the automotive industry.

Apparatuses and methods embodied herein may be employed during at least one of the stages of aircraft manufacturing and service method1000inFIG.10. In one illustrative example, components or subassemblies produced in component and subassembly manufacturing1006inFIG.10may be fabricated or manufactured in a manner similar to components or subassemblies produced while aircraft1100is in service1012inFIG.10. As yet another example, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during production stages, such as component and subassembly manufacturing1006and system integration1008inFIG.10. One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized while aircraft1100is in service1012, during maintenance and service1014inFIG.10, or both. The use of a number of the different illustrative embodiments may substantially expedite the assembly of aircraft1100, reduce the cost of aircraft1100, or both expedite the assembly of aircraft1100and reduce the cost of aircraft1100.

As used herein, the phrase “at least one of,” when used with a list of items, means different combinations of one or more of the listed items can be used, and only one of each item in the list may be needed. In other words, “at least one of” means any combination of items and number of items may be used from the list, but not all of the items in the list are required. The item can be a particular object, a thing, or a category.

For example, without limitation, “at least one of item A, item B, or item C” may include item A, item A and item B, or item B. This example also may include item A, item B, and item C or item B and item C. Of course, any combinations of these items can be present. In some illustrative examples, “at least one of” can be, for example, without limitation, two of item A; one of item B; and ten of item C; four of item B and seven of item C; or other suitable combinations.

As used herein, a first component “connected to” or “coupled to” or “associated with” a second component means that the first component can be connected directly or indirectly to the second component. The connection is a physical association. In other words, additional components may be present between the first component and the second component. The first component is considered to be indirectly connected to the second component when one or more additional components are present between the two components. When the first component is directly connected to the second component, no additional components are present between the two components.

For example, a first component can be considered to be physically connected to a second component by at least one of being secured to the second component, bonded to the second component, mounted to the second component, welded to the second component, fastened to the second component, or connected to the second component in some other suitable manner. The first component also can be connected to the second component using a third component. The first component can also be considered to be physically connected to the second component by being formed as part of the second component, an extension of the second component, or both.

The illustrative examples eliminate the need for three separate mechanisms with their own actuators and mechanism inputs and instead accomplishes all three tasks of unlocking deployable wings of an air launched vehicle, deploying deployable wings of an air launched vehicle from a stored position, and locking deployable wings of an air launched vehicle in a deployed position with one single linear actuation event.

The single command received by the disclosed wing lock and deployment apparatus causes the single linear actuation event which accomplishes all three tasks in sequential order.

The description of the different illustrative embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or limited to the embodiments in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Further, different illustrative embodiments may provide different features as compared to other desirable embodiments. The embodiment or embodiments selected are chosen and described in order to best explain the principles of the embodiments, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various embodiments with various modifications as are suited to the particular use contemplated.