Patent ID: 12196528

DETAILED DESCRIPTION OF THE DISCLOSURE

The foregoing summary, as well as the following detailed description of certain examples will be better understood when read in conjunction with the appended drawings. As used herein, an element or step recited in the singular and preceded by the word “a” or “an” should be understood as not necessarily excluding the plural of the elements or steps. Further, references to “one example” are not intended to be interpreted as excluding the existence of additional examples that also incorporate the recited features. Moreover, unless explicitly stated to the contrary, examples “comprising” or “having” an element or a plurality of elements having a particular condition can include additional elements not having that condition.

As described herein, examples of the present disclosure provide a launch system configured to interchangeably retain different types of stores, such as stores having different lengths. The launch system is configured to receive and releasably retain different types of stores, and launch or otherwise eject such stores without re-configuring the launch system. In at least one example, a launch system and method for an aircraft enable interchanging various lengths and types of stores onto a single launch system.

FIG.1illustrates a block diagram of a launch system100for an aircraft102, according to an example of the present disclosure. The aircraft102is a military aircraft, such as a military fighter jet, a bomber, or the like. As another example, the aircraft102is a helicopter. As another example, the aircraft102is an unmanned aerial vehicle, such as a drone.

The launch system100is configured to interchangeably and releasably retain different types of stores, such as air-to-air missiles, air-to-ground missiles, rockets, bombs, and/or the like. For example, a first store104is configured to be releasably retained by the launch system100. The launch system100is also configured to releasably retain one or more second stores106, which differ from the first store104. The first store104can be removed from the launch system100, and one or both of the second stores106can be secured to the launch system100in place of the first store104.

In at least one example, the first store104differs from the second stores106in terms of length. In particular, the first store104has a first length108, and each of the second stores106has a second length110, which is shorter than the first length108. In this manner, the first store104can be considered a long store, and the second stores106can be considered short stores. In at least one example, the second length110is half or approximately half (such as within 5%) the length of the first length108. Optionally, the second length110can be greater or less than half the first length108. For example, the second length110can be between 20-80% of the first length108.

The launch system100includes a first ejector112and a second ejector114. For example, the first ejector112is a forward ejector, and the second ejector114is an aft ejector, or vice versa. In at least one example, the first ejector112includes a first securing interface116having a first retainer118and a second retainer120. Similarly, the second ejector114includes a second securing interface122having a third retainer124and a fourth retainer126. The first ejector112and the second ejector114can be similarly configured, such that each of the first retainer118, the second retainer120, the third retainer124, and the fourth retainer126are of the same type and/or otherwise similarly configured.

The ejectors can be pyrotechnic, hydraulic, or pneumatic powered ejectors. Examples of the ejectors are shown and described in U.S. Pat. Nos. 11,459,102, and 11,505,318, each of which is entitled “Container Retention and Release Apparatus Having Integral Swaybrace and Retention Features.” However, such are merely examples of the ejectors. Other types of ejectors can be used.

The first retainer118is separated from the second retainer120by a distance128. Similarly, the third retainer124is separated from the fourth retainer126by a distance130. In at least one example, the distance128is equal to the distance130.

In at least one example, the first securing interface116is linearly aligned with the second securing interface122. For example, the first retainer118, the second retainer120, the third retainer124, and the fourth retainer126are all linearly aligned in relation to a common plane. In at least one example, the first retainer118, the second retainer120, the third retainer124, and the fourth retainer126are aligned along a common straight linear path.

The first ejector112and the second ejector114are configured to releasably retain the first store104. In at least one example, the first store104includes a first coupler132, a second coupler134, a third coupler136, and a fourth coupler138, which are linearly aligned with one another. The first coupler132is configured to be releasably retained by the first retainer118. The second coupler134is configured to be releasably retained by the second retainer120. The third coupler136is configured to be releasably retained by the third retainer124, and the fourth coupler is configured to be releasably retained by the fourth retainer126. As such, the first store104is configured to be releasably retained by both the first securing interface116of the first ejector112and the second securing interface122of the second ejector114.

In contrast, each of the second stores106is configured to be releasably retained by only one of the first securing interface116of the first ejector112or the second securing interface122of the second ejector114. For example, each of the second stores106includes a first coupler140and a second coupler142that is linearly aligned with the first coupler140. The first coupler140is configured to be releasably retained by the first retainer118(or the third retainer124), and the second coupler142is configured to be releasably retained by the second retainer120(or the fourth retainer126). In this manner, the launch system100can releasably retain two second stores106, with one second store106releasably retained by the first securing interface116of the first ejector112, and another second store106releasably retained by the second securing interface122of the second ejector114.

In at least one example, additional third stores can be releasably retained by single retainers. For example, third stores having lengths shorter than the length110can be releasably retained by each of the first retainer118, the second retainer120, the third retainer124, and/or the fourth retainer126.

In operation, the first store104can be interchangeably coupled to the launch system100with a plurality of the second stores106. For example, a single first store104can be releasably secured to both the first securing interface116of the first ejector112and the second securing interface122of the second ejector114. The first store104can then be removed from the launch system100, and one (such as a first) second store106can be releasably secured to the first securing interface116, and another (such as a second) second store106can be releasably secured to the second securing interface122. Accordingly, the same launch system100is used to releasably retain different stores (such as the first store104and the second stores106), such as having different lengths.

The couplers of the first store104and the second store106can be configured the same as one another. In at least one example, the couplers are bail lugs. In at least one other example, the couplers are retention posts. In at least one other example, the couplers are hangers. Such are examples, and the couplers can be various other features.

As described herein, the launch system100for the aircraft102includes the first ejector112and the second ejector114. The first ejector112and the second ejector114are configured to cooperate to releasably retain (that is, configured to release, such as by launching on command) the first store104having the first length108. That is, a single first store104is releasably retained by both the first ejector112and the second ejector114. Each of the first ejector112and the second ejector114is configured to releasably retain a second store106having a second length110that differs from the first length108. That is, a second store106is releasably retained by only one of the first ejector112or the second ejector114. In at least one example, the first ejector112is configured to releasably retain one second store106(such as the second store106ashown inFIG.11), and the second ejector114is configured to releasably retain another second store106(such as the second store106bshown inFIG.11).

The first ejector112and the second ejector114are configured to allow the first store104to be removed from the first ejector112and the second ejector114, and replaced with one or more of the second stores106. Further, the first ejector112and the second ejector114are configured to allow the one or more second stores106to be removed and replaced with the first store104.

In at least one example, the launch system100also includes a control unit150in communication with the first ejector112and the second ejector114, such as through one or more wired or wireless connections. The control unit150is also in communication with a launch device152, such as within a cockpit of an aircraft. The launch device152can be a trigger, button, or the like, such as can be on a yoke, joystick, or the like. The launch device152is configured to be engaged by a pilot to launch one or more of the stores104or106. For example, in response to engaging the launch device152, the control unit150receives a launch signal. The control unit150then operates the first ejector112and/or the second ejector114to launch either the first store104from the launch system100, or one or both of the second stores106, depending on which are releasably retained by the launch system100.

In at least one example, the control unit150is configured to communicate with the stores104and106to determine if the launch system100is carrying two second stores106or one first store104. In response to receiving the launch signal from the launch device152, the control unit150sends an electrical firing pulse to one or both of the first ejector112and/or the second ejector114(depending on the stores carried by the launch system100, and the launch command as output by the launch signal). For example, in the case of a second store106releasably secured to one of the first ejector112or the second ejector114, the control unit150sends an electrical pulse to the single first ejector112or second ejector114, which is retaining the second store106. In the case of a first store104releasably secured to both the first ejector112and the second ejector114, the control unit150simultaneously sends electrical pulses to both the first ejector112and the second ejector114.

As used herein, the term “control unit,” “central processing unit,” “CPU,” “computer,” or the like may include any processor-based or microprocessor-based system including systems using microcontrollers, reduced instruction set computers (RISC), application specific integrated circuits (ASICs), logic circuits, and any other circuit or processor including hardware, software, or a combination thereof capable of executing the functions described herein. Such are exemplary only, and are thus not intended to limit in any way the definition and/or meaning of such terms. For example, the control unit150may be or include one or more processors that are configured to control operation, as described herein.

The control unit150is configured to execute a set of instructions that are stored in one or more data storage units or elements (such as one or more memories), in order to process data. For example, the control unit150may include or be coupled to one or more memories. The data storage units may also store data or other information as desired or needed. The data storage units may be in the form of an information source or a physical memory element within a processing machine.

The set of instructions may include various commands that instruct the control unit150as a processing machine to perform specific operations such as the methods and processes of the various examples of the subject matter described herein. The set of instructions may be in the form of a software program. The software may be in various forms such as system software or application software. Further, the software may be in the form of a collection of separate programs, a program subset within a larger program, or a portion of a program. The software may also include modular programming in the form of object-oriented programming. The processing of input data by the processing machine may be in response to user commands, or in response to results of previous processing, or in response to a request made by another processing machine.

The diagrams of examples herein may illustrate one or more control or processing units, such as the control unit150. It is to be understood that the processing or control units may represent circuits, circuitry, or portions thereof that may be implemented as hardware with associated instructions (e.g., software stored on a tangible and non-transitory computer readable storage medium, such as a computer hard drive, ROM, RAM, or the like) that perform the operations described herein. The hardware may include state machine circuitry hardwired to perform the functions described herein. Optionally, the hardware may include electronic circuits that include and/or are connected to one or more logic-based devices, such as microprocessors, processors, controllers, or the like. Optionally, the control unit150may represent processing circuitry such as one or more of a field programmable gate array (FPGA), application specific integrated circuit (ASIC), microprocessor(s), and/or the like. The circuits in various examples may be configured to execute one or more algorithms to perform functions described herein. The one or more algorithms may include aspects of examples disclosed herein, whether or not expressly identified in a flowchart or a method.

As used herein, the terms “software” and “firmware” are interchangeable, and include any computer program stored in a data storage unit (for example, one or more memories) for execution by a computer, including RAM memory, ROM memory, EPROM memory, EEPROM memory, and non-volatile RAM (NVRAM) memory. The above data storage unit types are exemplary only, and are thus not limiting as to the types of memory usable for storage of a computer program.

As described herein, the launch system100includes two ejectors, such as the first ejector112and the second ejector114. The first ejector112and the second ejector114are configured to together releasably retain the first store104, and also each of the first ejector112and the second ejector114is configured to releasably retain a second store106. Accordingly, the launch system100is configured to carry a single first store104(for example, a long store) or two separate and distinct second stores106(for example, short stores). The launch system100allows a double quantity of second stores106to be carried in the space where a single first store104is carried.

Examples of the present disclosure provide the launch system100configured to interchangeably retain a single long store, such as the first store104, or two short stores, such as the second stores106, without re-configuring the aircraft102or the launch system100itself. The launch system100allows store configurations to be changed quickly without removing and replacing racks and launchers for each type of store. The launch system100improves overall integration of new weapons. The launch system100also reduces weapon drag in free flight. The launch system100also reduces weapons system structural weight. The launch system100also provides additional payload volume inside the weapons systems. The launch system100also provides additional weapon range performance. Further, the launch system100also reduces operational and maintenance costs, because multiple types of racks and launchers can be eliminated, minimized, or otherwise reduced.

FIG.2illustrates a flow chart of a method, according to an example of the present disclosure. Referring toFIGS.1and2, at200, the launch system100is secured to a portion of the aircraft102, such as to a lower surface of a wing or fuselage. At202, it is determined if a first store104is to be releasably secured to the launch system100. If so, the method proceeds to204, at which the first store104is secured to both the first ejector112and the second ejector114.

If, however, a first store104is not to be secured to the launch system100at202, the method proceeds to206, at which it is determined if one or more second stores106are to be secured to the launch system100. If not, the method ends at208.

If, however, one or more second stores106are to be secured to the launch system100, the method proceeds from206to210, at which a second store106is secured to the first ejector112or the second ejector114. In at least one example, one (such as a first) second store106is secured to the first ejector112, and another (such as a second) second store106is secured to the second ejector114.

At212, it is then determined if a first store212is to be secured to the launch system100. If not, the method ends at214.

If, however, a first store212is to be secured to the launch system100, the method proceed from212to216, at which the second store(s)106are removed from the first ejector112and the second ejector114. The method then return to204, at which the first store104is secured to the first ejector112and the second ejector114.

At218, it is then determined if one or more second stores106are to be secured to the launch system100. If not, the method ends at220.

If, however, one or more second stores106are to be secured to the launch system100, the method proceeds from218to222, at which the first store104is removed from the first ejector112and the second ejector114. The method then proceeds to210, as described above.

FIG.3illustrates a perspective front view of an aircraft102, according to an embodiment of the present disclosure. As shown, the aircraft102is a military fighter jet. The aircraft102includes a propulsion system302that includes two engines304, for example. Optionally, the propulsion system302may include more or less engines304than shown. The engines304are carried by wings306and/or a fuselage308of the aircraft102. In other examples, the engines304may be carried by other portions of the aircraft102, such as wings306. The fuselage308also supports horizontal stabilizers310and vertical stabilizers312. The fuselage308of the aircraft102includes the cockpit314covered by a canopy320. The launch system100(shown inFIG.1) is configured to be secured to a portion of the aircraft102, such as underneath a wing306, and/or the fuselage308. Optionally, the aircraft102may be various other types of military aircraft. For example, the aircraft102can be a military helicopter.

FIG.4illustrates a perspective view of a first store104, according to an example of the present disclosure. The first store104can be a missile, such as an air-to-air or air-to-land missile. Optionally, the first store104can be a rocket. As another example, the first store104can be a bomb.

The first store104includes a main body400. The first coupler132, the second coupler134, the third coupler136, and the fourth coupler138outwardly extend from the main body400. As shown, the couplers132,134,136, and138can be bail lugs.

FIG.5illustrates a perspective view of second stores106, according to an example of the present disclosure. One or both of the second stores106can be missiles, such as air-to-air or air-to-land missiles. Optionally, one or both of the second stores106can be rockets. As another example, one or both of the second stores106can be bombs.

The second stores106include main bodies402. The first couplers140and the second couplers142outwardly extend from the main bodies402. As shown, the couplers140and142can be bail lugs.

Referring toFIGS.4and5, the length108of the first store104is greater than the lengths110of the second stores106. Stated differently, the lengths110of the second stores106are less than the length108of the first store104.

FIG.6illustrates a perspective view of a first store104, according to an example of the present disclosure.FIG.7illustrates a perspective view of second stores106, according to an example of the present disclosure. Referring toFIGS.6and7, each of the couplers132,134,136,138,140, and142can be or otherwise include a pair of retention posts.

FIG.8illustrates a perspective view of a first store104, according to an example of the present disclosure.FIG.9illustrates a perspective view of second stores106, according to an example of the present disclosure. Referring toFIGS.8and9, the couplers161,162,163,164,171, and172can be or otherwise include cooperating hangers.

FIG.10illustrates a perspective view of a launch system100retaining a first store104, according to an example of the present disclosure. As shown, the first ejector112retains the first coupler132and the second coupler134of the first store104, and the second ejector114retains the third coupler136and the fourth coupler138of the of the first store104.

FIG.11illustrates a perspective view of the launch system100ofFIG.10retaining separate and distinct second stores106aand106b, according to an example of the present disclosure. The first ejector112retains the second store106a, and the second ejector112retains the second store106b, which his separate and distinct from the second store106a.

FIG.12illustrates a perspective view of a launch system100, according to an example of the present disclosure. In at least one example, the launch system100includes a carriage500having a housing502defining an internal chamber. At least portions of the first ejector112, the second ejector114, and the control unit150can be secured within the housing502. One or more lugs504outwardly extend from an outer surface of the carriage500. The lugs504are configured to secure to reciprocal features of an aircraft to secure the launch system100thereto. Optionally, the launch system100may not include a carriage or housing. Instead, the ejectors and control unit can be directly mounted to a portion of an aircraft.

FIG.13illustrates a perspective view of a launch system100, according to an example of the present disclosure. In this example, the launch system100includes an expanded carriage600that retains laterally aligned first ejectors112aand112b, and laterally aligned second ejectors114aand114b. As such, the launch system100can be configured to retain two first stores104in a side-by-side manner, or four different second stores106, as shown.

Further, the disclosure comprises examples according to the following clauses:

Clause 1. A launch system for an aircraft, comprising:a first ejector; anda second ejector,wherein the first ejector and the second ejector are configured to cooperate to releasably retain a first store having a first length, and wherein each of the first ejector and the second ejector is configured to releasably retain a second store having a second length that is less than the first length.

Clause 2. The launch system of Clause 1, wherein the first ejector is configured to releasably retain one second store, and wherein the second ejector is configured to releasably retain another second store.

Clause 3. The launch system of Clauses 1 or 2, wherein the first ejector and the second ejector are configured to allow the first store to be removed from the first ejector and the second ejector, and replaced with one or more of the second stores, and wherein the first ejector and the second ejector are further configured to allow the one or more second stores to be removed and replaced with the first store.

Clause 4. The launch system of any of Clauses 1-3, wherein the first ejector comprises a first securing interface having a first retainer and a second retainer, and wherein the second ejector comprises a second securing interface having a third retainer and a fourth retainer.

Clause 5. The launch system of Clause 4, wherein the first store is releasably retained by the first retainer, the second retainer, the third retainer, and the fourth retainer, and wherein the second store is releasably retained by only the first retainer and the second retainer, or the third retainer and the fourth retainer.

Clause 6. The launch system of Clauses 4 or 5, wherein the first retainer, the second retainer, the third retainer, and the fourth retainer are linearly aligned.

Clause 7. The launch system of any of Clauses 4-6, wherein the first store comprises:a first coupler releasably retained by the first retainer;a second coupler releasably retained by the second retainer;a third coupler releasably retained by the third retainer; anda fourth coupler releasably retained by the fourth retainer.

Clause 8. The launch system of any of Clauses 4-7, wherein the second store comprises:a first coupler releasably retained by one of the first retainer or the third retainer; anda second coupler releasably retained by one of the second retainer or the fourth retainer.

Clause 9. The launch system of any of Clauses 1-8, further comprising a control unit configured to operate the first ejector and the second ejector to launch the first store and the second store.

Clause 10. The launch system of Clause 9, wherein the control unit is configured to operate both the first ejector and the second ejector to launch the first store, and wherein the control unit is further configured to operate one of the first ejector or the second ejector to launch the second store.

Clause 11. The launch system of any of Clauses 1-10, further comprising a carriage configured to secure the launch system to the aircraft.

Clause 12. A launch method for an aircraft, comprising:releasably retaining a first store having a first length by a first ejector and a second ejector; andreleasably retaining a second store having a second length that is less than the first length with the first ejector or the second ejector.

Clause 13. The launch method of Clause 12, further comprising releasably retaining another second store with the other of the first ejector or the second ejector.

Clause 14. The launch method of Clauses 12 or 13, further comprising:removing the first store from the first ejector and the second ejector;replacing the first store with one or more of the second stores; andremoving the one or more second stores from one or both of the first ejector and the second ejector; andreplacing the one or more second stores with the first store.

Clause 15. The launch method of any of Clauses 12-14, further comprising operating, by a control unit, the first ejector and the second ejector to launch the first store and the second store.

Clause 16. The launch method of Clause 15, wherein said operating comprises:operating both the first ejector and the second ejector to launch the first store; andoperating one of the first ejector or the second ejector to launch the second store.

Clause 17. An aircraft comprising:a launch system including:a first ejector; anda second ejector,wherein the first ejector and the second ejector are configured to cooperate to releasably retain a first store having a first length, wherein the first ejector is configured to releasably retain a second store having a second length that is less than the first length, and wherein the second ejector is configured to releasably retain another second store having the second length,wherein the first ejector and the second ejector are configured to allow the first store to be removed from the first ejector and the second ejector, and replaced with the second stores, and wherein the first ejector and the second ejector are further configured to allow the second stores to be removed and replaced with the first store.

Clause 18. The aircraft of Clause 17, wherein the first ejector comprises a first securing interface having a first retainer and a second retainer, wherein the second ejector comprises a second securing interface having a third retainer and a fourth retainer, and wherein the first retainer, the second retainer, the third retainer, and the fourth retainer are linearly aligned.

Clause 19. The aircraft of Clause 18, wherein the first store is releasably retained by the first retainer, the second retainer, the third retainer, and the fourth retainer, wherein one of the second stores is releasably retained by only the first retainer and the second retainer, and wherein the other of the second stores is releasably retained by only the third retainer and the fourth retainer.

Clause 20. The aircraft of any of Clauses 17-19, wherein the launch system further comprises a control unit configured to operate the first ejector and the second ejector to launch the first store and the second store, wherein the control unit is configured to operate both the first ejector and the second ejector to launch the first store, and wherein the control unit is further configured to operate one of the first ejector or the second ejector to launch the second store.

As described herein, examples of the present disclosure provide systems and methods for interchanging different stores in relation to a single launch system. Further, examples of the present disclosure provide adaptable and interchangeable launch systems and methods configured to releasably retain different types of stores.

While various spatial and directional terms, such as top, bottom, lower, mid, lateral, horizontal, vertical, front and the like can be used to describe examples of the present disclosure, it is understood that such terms are merely used with respect to the orientations shown in the drawings. The orientations can be inverted, rotated, or otherwise changed, such that an upper portion is a lower portion, and vice versa, horizontal becomes vertical, and the like.

As used herein, a structure, limitation, or element that is “configured to” perform a task or operation is particularly structurally formed, constructed, or adapted in a manner corresponding to the task or operation. For purposes of clarity and the avoidance of doubt, an object that is merely capable of being modified to perform the task or operation is not “configured to” perform the task or operation as used herein.

It is to be understood that the above description is intended to be illustrative, and not restrictive. For example, the above-described examples (and/or aspects thereof) can be used in combination with each other. In addition, many modifications can be made to adapt a particular situation or material to the teachings of the various examples of the disclosure without departing from their scope. While the dimensions and types of materials described herein are intended to define the aspects of the various examples of the disclosure, the examples are by no means limiting and are exemplary examples. Many other examples will be apparent to those of skill in the art upon reviewing the above description. The scope of the various examples of the disclosure should, therefore, be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. In the appended claims and the detailed description herein, the terms “including” and “in which” are used as the plain-English equivalents of the respective terms “comprising” and “wherein.” Moreover, the terms “first,” “second,” and “third,” etc. are used merely as labels, and are not intended to impose numerical requirements on their objects. Further, the limitations of the following claims are not written in means-plus-function format and are not intended to be interpreted based on 35 U.S.C. § 112(f), unless and until such claim limitations expressly use the phrase “means for” followed by a statement of function void of further structure.

This written description uses examples to disclose the various examples of the disclosure, including the best mode, and also to enable any person skilled in the art to practice the various examples of the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the various examples of the disclosure is defined by the claims, and can include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if the examples have structural elements that do not differ from the literal language of the claims, or if the examples include equivalent structural elements with insubstantial differences from the literal language of the claims.