阅读说明：本技术 从附接毂展开的柔性卫星 (Flexible satellite deployed from an attachment hub ) 是由 C·M·科斯纳 M·S·鲍德温 于 2018-07-31 设计创作，主要内容包括：一种示例性卫星,其包括通过柔性悬臂彼此耦接的一对有效载荷,其中,该柔性悬臂被配置为使得该对有效载荷能够容易地与相关联的附接毂手动接合,并且还提供一被动释放力用于从附接毂向外的方向展开至少一个有效载荷。当柔性悬臂挠曲以将有效载荷附接至附接毂时,柔性悬臂中存储的应变能将作为用于实现被动释放的势能。当至少一个有效载荷从附接毂释放时,该应变能将会释放。附加的有效载荷可以与该对有效载荷串联附接,其中柔性悬臂用于附接相邻的有效载荷。这些附加的有效载荷可以通过非复杂的或复杂的附接机构从附接毂上释放。(An exemplary satellite includes a pair of payloads coupled to each other by a flexible cantilever, wherein the flexible cantilever is configured to enable the pair of payloads to easily manually engage an associated attachment hub and also provide a passive release force for deploying at least one payload in an outward direction from the attachment hub. When the flexible cantilever is flexed to attach a payload to the attachment hub, the stored strain energy in the flexible cantilever will serve as potential energy for achieving passive release. When the at least one payload is released from the attachment hub, the strain energy will be released. An additional payload may be attached in series with the pair of payloads, with a flexible cantilever arm used to attach adjacent payloads. These additional payloads may be released from the attachment hub by uncomplicated or complex attachment mechanisms.)

1. A satellite, comprising:

a pair of payloads; and

a flexible cantilever extending between and coupled to each payload,

wherein the satellite is configured to engage an attachment hub by flexing the cantilever and provide a passive release force for releasing the satellite from the attachment hub.

2. The satellite of claim 1, wherein the passive release force passively separates at least one of the payloads outward from the attachment hub.

3. The satellite of any one of claims 1 or 2, wherein flexure of the cantilever allows each of the payloads to be attached spaced apart from one another about the hub.

4. The satellite of any one of claims 1-3, wherein the flexible cantilever has a single resting position.

5. The satellite of any one of claims 1-4, wherein the flexible cantilevers extend along a non-linear central path between the payloads.

6. The satellite of any one of claims 1-5, wherein the flexible cantilever is a hingeless cantilever.

7. The satellite of any one of claims 1-6, wherein at least one of the payloads comprises an attachment mechanism configured to detachably release the payload from the attachment hub without applying a force to the payload to cause the payload to deploy outward from the attachment hub.

8. The satellite of any one of claims 1-7, wherein the cantilevers in all configurations allow for continuous thermal, RF, or electrical connections between the payloads.

9. The satellite of any of claims 1-8, wherein the cantilever is configured in all configurations to prevent physical engagement of the payloads with one another.

10. The satellite of any one of claims 1-9, further comprising a third payload and a second flexible boom extending between and coupled to the third payload and one of the pair of payloads, and wherein the satellite comprises three payloads and two flexible booms, the satellite configured to engage with the attachment hub by flexing both booms and provide a passive release force for releasing the satellite from the attachment hub.

11. A satellite assembly comprising an attachment hub having a plurality of ports and the satellite of any of claims 1-10, wherein at least one payload of the pair of payloads is attached to the attachment hub at one of the ports.

12. A satellite, comprising:

a pair of payloads each having an attachment portion for attachment to a port of an attachment hub, respectively; and

a cantilever extending between and coupled to each payload of the pair of payloads, wherein the cantilever is configured to transition between a biased state for attachment to the attachment hub and a default state for at least partial deployment outward from the attachment hub upon release of the stored energy.

13. The satellite of claim 12, wherein the payloads are less spaced from one another when the cantilever is in the biased state than when in the default state.

14. The satellite of any one of claims 12 or 13, wherein the cantilever is configured such that it has a single default state.

15. The satellite of any one of claims 12 to 14, wherein the cantilevers in all states are configured to allow continuous thermal, RF, or electrical connections between the payloads.

16. The satellite of any of claims 12-15, wherein the cantilevers in all states are configured to prevent physical engagement of the payloads with one another.

17. The satellite of any one of claims 12-16, further comprising a third payload and a second cantilever extending between and coupled to the third payload and one of the pair of payloads, and wherein the second cantilever is configured to transition between a biased state for attachment to the attachment hub and having stored energy and a default state for at least partial deployment outward from the attachment hub upon release of the stored energy.

18. A method of deploying a satellite from an attachment hub, the method comprising the steps of:

providing a satellite having a pair of payloads with a flexible cantilever extending between the pair of payloads, and each of the payloads coupled to an attachment hub by an attachment mechanism;

releasing the attachment mechanism, the attachment mechanism selectively attaching a first payload of the payloads relative to an attachment hub; and

transitioning the flexible cantilever from a biased state having a stored strain energy to a default state, thereby causing the first payload to deploy outward from the attachment hub by the stored strain energy released by the flexible cantilever.

19. The method of claim 18, wherein releasing the stored strain energy from the flexible cantilever comprises changing the cantilever from a deflected state in a biased state to an undeflected state.

20. The method according to any one of claims 18 or 19, further comprising the step of: releasing the attachment mechanism that selectively couples the first payload to the attachment hub without having to apply a force to the first payload that would cause the first payload to deploy outward from the attachment hub.

Technical Field

The present invention relates generally to a satellite deployed from an attachment hub, and more particularly to a flexible minisatellite attached to and deployed outwardly from an ESPA-like hub, and methods of attaching and deploying the flexible minisatellite to and from an ESPA-like hub.

Background

The development of small satellites (also known as minisatellites) requires a lot of compliance and their list is very long, including weight, volume, mass, size, spacing, etc. These requirements often result in the need for low power, low heat dissipation specifications, which in turn reduces the mission utility of the microsatellite. These requirements also typically result in a dense packing of the loading and deployment equipment.

For example, where a satellite has a payload that is attachable to and deployable from an evolved consumable launch vehicle (EELV) secondary payload adapter (ESPA), these payload modules must comply with many of the requirements listed above. A deployed satellite may include a number of payloads interconnected in some manner and in an attached and deployed state. The interconnection itself may limit the utility of the task due to the need to stabilize the payload modules relative to each other after deployment, or to engage the payload modules with each other. Thus, typically, the interconnect device requires moving parts, which in turn may limit or completely prevent connectivity (e.g., electrical connectivity, thermal connectivity, RF connectivity, and power connectivity) between the payload modules in one or more respects.

Furthermore, each payload module requires a deployment mechanism, and typically the complexity of such a deployment mechanism is increased compared to the interconnectivity of the payload modules. One example of a deployment mechanism is Lightband from Planet systems corporation, which is mechanically complex and expensive. In these examples, complexity typically increases weight, mass, volume, power requirements, cost, and the number of components that risk failure.

Disclosure of Invention

The present disclosure provides an exemplary satellite that can be attached to and deployed outward from an attachment hub, such as an ESPA-like hub, and that addresses many of the previously listed issues. The exemplary satellite includes at least one pair of payload modules (also referred to as payloads) coupled to each other by a flexible member. The flexible member is configured to meet torque on the ESPA interface, stiffness requirements when attached to the ESPA hub, and stiffness requirements when deployed. The flexible member enables a continuous connection to be maintained between adjacent payloads thereby eliminating the need for complex systems to engage each other with payloads to establish such a connection. In addition, the flexible member facilitates deployment of one or more payloads, thereby reducing or completely eliminating the need for one or more complex and expensive deployment mechanisms.

An exemplary satellite, comprising: a pair of payloads coupled to each other by a flexible cantilever, wherein the flexible cantilever is configured to enable the pair of payloads to be easily manually engaged with an associated attachment hub and also provide a passive release force for deploying at least one payload in an outward direction from the attachment hub. When the flexible cantilever is flexed to attach a payload to the attachment hub, the stored strain energy in the flexible cantilever will serve as potential energy for achieving passive release. When at least one payload is released from the attachment hub, the strain energy will be released, which can be done by a non-complex, non-unusual attachment mechanism. An additional payload may be attached in series with the pair of payloads, with a flexible cantilever arm used to attach adjacent payloads. These additional payloads may be released from the attachment hub by a complex non-complex attachment mechanism.

According to one aspect, a satellite is disclosed that includes a pair of payloads and a flexible boom extending between and coupling the payloads. The satellite is configured to engage the attachment hub through flexure of the cantilever and provide a passive release force for releasing the satellite from the attachment hub.

The passive release force may cause the at least one payload to passively detach outwardly from the attachment hub.

The flexing of the cantilever arms may allow the individual payloads to be attached to the hub spaced apart from one another about the hub.

The flexible cantilever may have a single (single) rest position.

The flexible cantilevers may extend along a non-straight line (non-linear) center path between the payloads.

The flexible cantilever may be a hingeless cantilever.

At least one of the payloads may include a coupler configured to enable the payload to be decoupled from the attachment hub without applying a force to the payload such that the payload is spaced outwardly from the attachment hub.

The cantilevers in all configurations may allow for continuous thermal, RF, or electrical attachment between payloads.

The cantilevers in all configurations may be configured to prevent the payloads from physically engaging each other.

The satellite may further comprise a third load and a second flexible cantilever extending between and coupling the third load and one of the pair of loads, wherein the satellite comprising the three loads and the two flexible cantilevers is configured to engage the attachment hub by flexing the two cantilevers and provide a passive release force for releasing the satellite from the attachment hub.

The satellite may be coupled with an attachment hub having a plurality of ports, wherein at least one payload of the pair of payloads is attached to the attachment hub at one of the ports.

According to another aspect, a satellite is disclosed that includes a pair of payloads, wherein each payload has an attachment for attachment to a port of an attachment hub; and a coupling member extending between and coupling each payload of the pair of payloads, wherein the coupling member is configured to transition between a biased state for attachment to the attachment hub and the coupling member has stored energy and a default state after release of the stored energy for at least partially deploying the payloads outward from the attachment hub.

When the coupling member is in the biased state, the payloads are spaced further apart from one another than when in the default state.

The coupling member may be configured such that it has a single default state.

The coupling members in all states may be configured to allow continuous thermal, RF or electrical connection between payloads.

The coupling members in all states may be configured to prevent the payloads from physically engaging each other.

The satellite may further include a third payload and a second coupling member extending between and coupling the third payload and one of the pair of payloads, wherein the second coupling member is configured to transition between a biased state for attachment to the attachment hub and the second coupling member has stored energy and a default state after release of the stored energy for the attachment hub to at least partially deploy the payload outwardly.

According to another aspect, a method of deploying a satellite from an attachment hub is disclosed, comprising the steps of: (a) providing a satellite having a pair of payloads with a flexible boom extending therebetween and each payload coupled to an attachment hub; (b) releasing the attachment of one of the payloads to the attachment hub; and (c) transitioning the flexible cantilevers from the biased state having the stored strain energy to a default state, whereby release of the stored strain energy by the flexible cantilevers causes one of the payloads to deploy outward from the attachment hub.

Releasing the stored strain energy from the flexible cantilever may include changing the cantilever from a deflected state in a biased state to an undeflected state.

The method may further comprise the steps of: the coupling member is released, which selectively couples the payload to the attachment hub without applying a force to the payload that would cause the payload to deploy outward from the attachment hub.

To the accomplishment of the foregoing and related ends, the invention, then, comprises the features hereinafter fully described and particularly pointed out in the claims. The following description and the annexed drawings set forth in detail certain illustrative embodiments of the invention. These embodiments are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the drawings.

Drawings

The following drawings, which are not to scale, illustrate various aspects of the disclosure.

FIG. 1 is a schematic view of an aerospace vehicle including a satellite in accordance with the invention;

FIG. 2 is an orthogonal view of an exemplary satellite attached to an attachment hub, in accordance with the present invention;

FIG. 3 is another orthographic view of the satellite of FIG. 2;

FIG. 4 is a front view of an exemplary release mechanism for attaching the satellite of FIG. 2 to an attachment hub;

FIG. 5 is a partial view of the release mechanism of FIG. 4 shown in section A-A of FIG. 4;

FIG. 6 is a cross-sectional view of the release mechanism of FIG. 4 taken along line B-B of FIG. 4;

FIG. 7 is an elevation view of the satellite of FIG. 2 attached to the attachment hub of FIG. 2;

FIG. 8 is an elevation view of the satellite of FIG. 2, showing the satellite at least partially deployed from the attachment hub;

FIG. 9 is an elevation view of the satellite of FIG. 2, showing the satellite fully deployed from the attachment hub;

FIG. 10 is an elevation view of the satellite of FIG. 2, with the satellite separated from the attachment hub;

FIG. 11 is a schematic view of the satellite of FIG. 2 in an unfolded state;

FIG. 12 is a schematic view of the satellite of FIG. 2 in a stowed state;

FIG. 13 is an orthogonal view of another exemplary satellite according to the present disclosure, wherein the satellite is attached to an attachment hub;

FIG. 14 is another orthogonal view of the satellite shown in FIG. 13;

FIG. 15 is an elevation view of the satellite of FIG. 13, showing the satellite attached to the attachment hub of FIG. 13;

fig. 16 is an elevation view of the satellite of fig. 13, separated from the attachment hub.

Detailed Description

The present disclosure is generally directed to a satellite for deployment in aerospace from an attachment hub, the deployment typically occurring outside the atmosphere of the planet, which may be, for example, an ESPA-like hub carried into outer space by an ESPA-like vehicle. The present disclosure more particularly relates to a flexible moonlet attached to and deployed outwardly from an ESPA-like hub, and methods of attaching and deploying the flexible moonlet to and from an ESPA-like hub.

The present invention provides a satellite that is easily attached to an attachment hub and reduces the cost and complexity of a deployment mechanism for detaching and deploying the satellite from the attachment hub while meeting the necessary standards and requirements for the onboard satellite being brought into space by an aerospace vehicle. Although the invention is generally directed to so-called small satellites (which are typically smaller in mass and size than large satellites), such as those weighing less than about 500kg (about 1100 pounds) — the invention is equally applicable directly to satellites of various sizes, whether large or small. The invention may also be used to release modules in other release environments, such as in the atmosphere, underwater, etc.

FIG. 1 illustrates an exemplary aerospace vehicle 10 for carrying equipment out of the planet's atmosphere and transporting to a release environment having low or no atmospheric pressure, low or no gravitational forces, or what is commonly referred to as outer space. The vehicle 10 may be used to transport a satellite 12 according to the present disclosure into a release environment when attached to an attachment hub 14.

Vehicle 10 includes a fuselage (not shown) attached to one or more thrusters 16. The booster 16 includes a nozzle 18, the nozzle 18 being used to direct the propulsion gas out of the booster 16. The fuselage is positioned within the fairing 20 and has one or more attachment hubs 14 attached thereto. The fuselage may also have attached to it one or more vehicles to be released in the release environment, such as a host vehicle 15, such as a satellite, also located within the fairing 20. Although in some embodiments the one or more attachment hubs 14 and satellites 12 may be directly attached to the host-vehicle 15, in the embodiment shown herein the attachment hubs 14 and satellites 12 are not directly attached to the host-vehicle 15. In some embodiments, more than one host vehicle 15 may be included in the vehicle 10, or the host vehicle 15 may be omitted.

The fairing 20 is removably releasable relative to the fuselage and protects the host vehicle 15, the attached hub 14, and the satellite 12 attached to the hub 14 during transport. The fairing 20 may include a nose cone 22, or the nose cone 22 may be attached to the fuselage and separate from the fairing 20. The fairing 20 is configured to be detachable in any suitable manner to allow the attachment hub 14 (and the satellite 12 attached to the hub 14) to be detached from the rest of the vehicle 10 in a suitable release environment.

Referring to fig. 2 and 3, an exemplary satellite assembly 24 is shown, for example, for use with the vehicle 10 of fig. 1. The depicted satellite assembly 24 includes an attachment hub 14 and satellites 12 at attachment locations (e.g., ports 26) respectively attached to the hub 14. The satellite 12 includes a plurality of payloads 30 coupled to one another. In particular, the illustrated satellite 12 includes a pair of payloads 30, the pair of payloads 30 coupled to one another by a coupling member 32. Each payload 30 (which may also be referred to as a payload module or module) is attached to a port 26 on the attachment hub 14, respectively.

The attachment hub 14 may be any suitable structure that can be used to stabilize one or more payloads 30 of one or more satellites 12 during transport to a release environment. The depicted attachment hub 14 is an evolved consumable launch vehicle (EELV) secondary payload adapter (ESPA) hub having a substantially rigid and annular structure (e.g., annular in shape). The attachment hub 14 is made of any suitable material, such as metal (e.g., lightweight metal). A plurality of ports 26 are provided around the annular hub. The illustrated attachment hub 14 includes four ports 26 equally spaced around the circumference of the attachment hub 14. Each port 26 includes a radially outwardly projecting rim 40 for supporting attachment of a payload 30 of the satellite 12. One aperture 42 is defined by each port 26. Each port 26 defines a bore 42, wherein each bore 42 extends completely through an annular ring body 46 of the attachment hub 14 from a radially outer surface 44 of the annular ring body 46 to a radially inner surface 48 of the annular ring body 46. The upper and lower collars 50 extend radially outward at opposite axial ends 52 and 54, respectively, of the annular body 46.

Each port 26 is generally circular and has the same dimensions. Each port 26 is equally spaced from the oppositely disposed axial ends 52 and 54. The same size and spacing provided by the ports 26, and the spacing therebetween, facilitate a balance of forces around the attachment hub 14 and uniform attachment of the various satellites 12. It should be understood that in other embodiments, the ports 26 may have other sizes, shapes, and different positions relative to each other. A different number of ports 26 may also be included, such as 1 or more.

Although reference is made herein to the satellite 12 being configured to be attached to the attachment hub 14 and deployed from the attachment hub 14, in other embodiments, not all of the payload 30 or the satellite 12 must be detached from the attachment hub 14. Conversely, in some tasks, one or more attached payloads 30 of a satellite 12 may remain attached to an attachment hub 14, while one or more other payloads 30 coupled to the attached payload 30 may be released from the attachment hub 14 in the proper sequence while remaining at least partially coupled to one or more of the attached payloads 30.

The depicted satellite 12 is configured to engage the attachment hub 14 by flexing (flex) the coupling member 32 and provide a passive release force for releasing the satellite 12 from the attachment member 14. The passive release force provides a passive separation of at least one payload 30 of the satellite 12 outwardly from the attachment hub 14. In this manner, the satellite 12 need not be provided with a complex release and deployment mechanism for release and deployment of the at least one payload 30, as will be described in further detail below.

Typically, a pair of payloads 30 of a satellite 12 is required to have a limited payload volume, mass, and weight. Although payload 30 is schematically depicted as rectangular, payload 30 may have any suitable shape, such as to conform to dimensional requirements for use with a particular attachment hub or a particular task. For example, payload 30 may have a volume no greater than a range of about 4 feet cubic to about 1 feet cubic, or in another example, about 3 feet cubic to about 2 feet cubic, or in another example, a volume of, for example, about 24 inches by about 28 inches by about 38 inches, and thus in any embodiment, its width, length, and height need not be equal to each other. Different payloads 30 may also have different loading volumes.

Payload 30 may include any necessary equipment for accomplishing a task, such as visual, audio, imaging, power supply, communication, propulsion, command, and control equipment. The devices may include, for example, mechanical, electrical, chemical, RF, chemical, and thermal components. Specific examples of devices may include remote imaging cameras, antennas, repeaters, batteries, fuel, solar panels, or scientific experimental devices.

Support of the payloads 30 relative to each other during loading, deployment and post-deployment of the payloads 30 is provided by the coupling members 32. The coupling member 32 is configured to allow the at least one payload 30 to be passively released outwardly from the port 26 of the attachment hub 14. The coupling member 32 allows the passive release to be achieved in view of the coupling member 32 being a flexible coupling member.

For example, the illustrated coupling member 32 is a flexible cantilever 32 that extends between and couples together the payloads 30 in a pair of payloads 30. The cantilever 32 is generally cylindrical and extends along a linear central path 64 between opposite ends 66 and 68 of the cantilever 32. The linear central path 64 is non-linear and includes a bend 69. The curved portion 69 may be, for example, an acute angle having a single apex, or may be, for example, a curved line having a plurality of apexes.

The curved portion 70 of the cantilever 32 corresponds to the curved portion 69 and is located between the opposite ends 66 and 68, such as at a midpoint of the cantilever 32. Thus, the cantilever 32 is a curved cantilever having a curved portion 79, wherein the curved portion 70 is disposed between the oppositely extending cantilever portions 72. The cantilever portions 72 are shown to be of the same size and length and are generally linear until transitioning to the bend 70. The exemplary cantilever 32 may be solid or hollow, e.g., having a centrally extending cavity.

In other embodiments, the cantilever 32 may include one or more of any of the following features: the additional bends 70, the two or more cantilever portions 72, or the cantilever portions 72 have different shapes, diameters, or lengths. In some embodiments, the cantilevered portion 72 may not be straight. In some embodiments, the bend 70 may not be disposed at the midpoint of the flexible cantilever 32.

The oppositely disposed ends 66 and 68 of the boom 32 are each attached to a different payload 30 to separate the payloads 30 from one another. Ends 66 and 68 may be rigidly coupled with payload 30, such as fixedly coupled to payload 30, by fasteners, welding, adhesives, other mechanical coupling means, or any combination thereof. Other coupling methods may also be suitable for this.

The exemplary boom 32 has a central linear path 64 with a chord length in a range of about 8 feet to about 2 feet, or about 7 feet to about 3 feet, or about 6 feet to 5 feet (e.g., about 5.5 feet).

The exemplary cantilever 32 has a uniform diameter along the length of the path 64. For example, the diameter of the cantilever 32 may be in the range of about 12 inches to about 2 inches, or in the range of about 10 inches to about 4 inches, or in the range of about 8 inches to about 6 inches (e.g., about 7 inches).

The cantilever 32 may be made of any suitable material to provide sufficient rigidity and minimal flexibility. Cantilever 32 may comprise, for example, graphite, aluminum, beryllium, carbon fiber, or glass fiber. The flexibility of cantilever 32 is affected by the material, size, and overall shape of cantilever 32.

The flexing of the cantilever 32 enables the cantilever 32 to move (by flexing) to a biased state to allow each payload 30 of a pair of payloads 30 spaced around the attachment hub 14 to be attached to the attachment hub 14. In particular, the cantilever 32 may be flexibly biased to a biased state to attach the satellite 12 to the port 26 of the attachment hub 14. In the biased state, the flexible cantilever 32 retains strain energy therein that is preloaded in the cantilever 32 due to deflection of the cantilever 32 from the unbiased default position to the biased position. The release of the strain energy will allow the satellite 12 to deploy at least partially outward from the attachment hub 14, e.g., allowing one of the payloads 30 to passively release outward from the respective port 26 after the respective payload 30 is disconnected from the port 26. In this manner, the respective payload 30 is positioned spaced from the attachment hub 14 after passive release thereof occurs.

When the stored strain energy is released, the flexible cantilever 32 quickly transitions from the biased state of the cantilever 32 to the default state. In one embodiment, the transition may include displacing the end 66 or 68 of the flexible cantilever along a central plane that bisects the cantilever 32 and extends along the central linear path 64. The transition causes payload 30 to move to a position away from cantilevers 32, further away from cantilevers 32 when in the default state than cantilevers 32 when in the biased state. This transition results in a linear movement of the displaced end 66 or 68 in plane of about 1mm to about 10mm, or about 2mm to about 8mm, or about 3mm to about 7mm, or about 4mm to about 6mm (e.g., about 5 mm). For example, the cantilever 32 may require less bending on an attachment hub 14 having a larger diameter to enable attachment of the payload 30 than would be the case for an attachment hub having a smaller diameter. This minimal movement enables each cantilever portion 72 to minimally increase the angle between them when transitioning from the biased state to the default state of cantilever 32.

The cantilever 32 is configured such that it has a single rest length and a single default state (also referred to as a rest (rest) state). Also, the cantilever 32 is hingeless, which at least partially allows the single resting length to be achieved. As a result, the cantilevers 32 in all configurations (e.g., in the biased state, the default state, and the transition state therebetween) can prevent the payloads 30 in a pair of payloads 30 from physically engaging each other such that the payloads 30 are spaced apart from each other in all configurations of the cantilevers 32.

Although the boom 32 is flexible, the boom 32 is also configured to provide sufficient stiffness to the satellite 12, as described above. The cantilever 32 is sufficiently rigid to separate from the attachment hub 14 during deployment operations, for example, to have sufficient rigidity to freely fly (free-flying) or freely maneuver the satellite 12. Because of these characteristics, when the satellite 12 is in the detached state (and the flexible cantilevers 32 are in the default state), it is no longer necessary to mate the payloads 30 to one another after deployment to maintain the necessary operational stiffness.

Likewise, the boom 32 also allows the satellite 12 to meet stiffness requirements when attached to the attachment hub 14 (e.g., when stowed during a transition of launching the vehicle 10 and the vehicle 10 into a release environment). For example, when detached from the attachment hub 14, the satellite 12 is shown having a natural resonant frequency (detachment frequency) of a free-free two-body system (two-body system) with two masses and one spring element (spring) in between. When the flexible cantilevers 32 flex to allow the satellite 12 to be attached to the attachment hub 14, the depicted satellite 12 has the second frequency (attachment frequency) of the two-mass three-spring-element system after being attached to the attachment hub 14.

The resonant frequency of the detached satellite 12 may be about 30% to about 5% of the resonant frequency when attached to the attachment hub, or about 20% to about 5% of the resonant frequency when attached to the attachment hub, or when the ratio of the detached resonant frequency to the attached resonant frequency is about 1: 10. The cantilever 32 is configured by its shape, size and material to provide such a ratio of detached resonant frequency to attached resonant frequency.

In one embodiment, the satellite 12 may have a decoupling resonant frequency in the range of about 1Hz to about 5Hz, or in the range of about 2Hz to about 4Hz, or about 3.5Hz or about 3.0 Hz. In such embodiments, the attachment resonant frequency of the satellite 12 may be in the range of about 10Hz to about 50Hz, or in the range of about 20Hz to about 40Hz, or about 30Hz or about 35 Hz.

Whereas the flexible boom 32 is hingeless and has a single default or rest state, the boom 32 allows for continuous attachment between payloads 30 in a pair of payloads 30. The cantilever 32 of all configurations herein, for example, the flexible cantilever 32, allows for continuous thermal, electrical, power and RF connections. This aspect of the satellite 12 greatly increases the mission utility compared to conventional satellites (with extended hinge attachments between respective payloads).

Referring to fig. 4-7, the payloads 30 are each attached to a respective port 26 by a respective attachment mechanism 80 (also referred to herein as a release mechanism). Each attachment mechanism 80 physically couples an attachment portion 82 of a respective payload 30 to an edge 40 of a respective port 26. Given that the preloaded strain energy can be transferred from the curved cantilever 32 to the disconnected payload 30 when the payload 30 is decoupled from the hub 14, the satellite 12 need not include two complex attachment mechanisms 80 for attaching two payloads 30 to the attachment hub 14. Rather, satellite 12 may include one complex attachment mechanism 106 and one uncomplicated, extraordinary attachment mechanism 84, the differences of which will be discussed in further detail.

For example, generally, attachment mechanism 84 has fewer components and actuators, lower power requirements, and lower cost than a complex and unusual alternative attachment mechanism such as a Lightband. The depicted satellite 12 includes at least one uncomplicated, unusual attachment mechanism 84 that is relatively inexpensive in cost. The non-complex attachment mechanism 84 may be attached to the respective attachment portion 82 of the respective payload 30. In other embodiments, the uncomplicated attachment mechanism 84 may be isolated from the satellite 12, for example, by attaching the satellite 12 to the respective port 26 of the attachment hub 14 prior to attaching it to the attachment hub 14.

Referring specifically to fig. 4-6, an exemplary non-complex attachment mechanism 84 is shown. The attachment mechanisms 84 are configured to removably release the respective payloads 30 from the attachment hubs 14 without applying a force to the payload 30 that would cause the payload 30 to deploy outward from the attachment hubs 14. Instead, the mechanism 84 (such as a modified barrel ring) is configured to be merely detached to release the attachment with the respective rim 40 and the respective attachment portion 82. Although only one exemplary mechanism 84 is shown herein, suitable alternative mechanisms may be used in some embodiments.

The exemplary mechanism 84 includes two separable halves 85. Each half 85 includes a band 86 having a semi-annular shape and a grooved section 88 extending radially inward from the band 86. The grooved sections 88 may be integral with the belt 86 or attached to the belt 86 in any suitable manner. The half 85 is attached to the strap 86 by any suitable means. The halves 85 are connected to each other by connectors 92, each connector 92 comprising a set of fittings 94, the sets of fittings 94 being connected to form the connector 92. The illustrated mechanism 84 includes a pair of links 92, the links 92 being oppositely disposed at circumferentially opposite locations thereof relative to the annular shape of the mechanism 84. The fitting 94 of each connector 92 is attached to the fitting 94 in the other connector 92 by the strips 86 and slotted sections 88 of the respective half 85. A joint 96 extends between the fittings 94 of each connector 92. Release of one or both ends of the joint 96 causes the two halves 85 to separate from each other, thereby disconnecting the payload 30 from the port 26.

More specifically, the grooved sections 88 are configured to receive and retain axially adjacent annular rings 98 and 100. One of the annular rings 98 and 100 may be integral with or otherwise attached to one of the rim 40 or the attachment portion 82. The other of the annular rings 98 and 100 is integral with or otherwise attached to the other of the rim 40 or the attachment portion 82. The radially outer keys 102 and 104 of the annular rings 98 and 100, respectively, are shaped to be received in the grooved sections 88. The groove segments 88 are V-shaped and the radially outer keys 102 and 104 of the annular rings 98 and 100 together form a corresponding V-shape. In some embodiments, the keys and slots may have any other suitable corresponding shape.

Release of one or both connectors 92 of attachment mechanism 84 disconnects payload 30 and port 26, i.e., annular rings 98 and 100 are separated from each other when they are not held adjacent to each other by slotted section 88. The release of the link 92 may be by any suitable method, such as mechanical, electromechanical or chemical means.

Referring to fig. 7, another payload 30 is attached to a corresponding port 26 of the attachment hub 14 by a typical, more complex attachment mechanism 106. The more complex attachment mechanism 106 couples the attachment portion 82 of the respective payload 30 with the edge 40 of the respective port 26. The depicted satellite 12 includes attachment mechanisms 106 that attach to respective attachment portions 82 of respective payloads 30. In other embodiments, the complex attachment mechanism 106 may be isolated from the satellite 12, such as by attaching the satellite 12 to the respective port 26 of the attachment hub 14 prior to attaching it to the attachment hub 14.

Referring to fig. 7-10, the satellite 12 is shown deployed from the attachment hub 14 in sequence. The attachment mechanisms 80 are released sequentially with the attachment mechanism 84 being released prior to the attachment mechanism 106.

In fig. 7, the satellite 12 is attached to an attachment hub 14. Each attachment mechanism 80 includes: an attachment mechanism 84 and an attachment mechanism 106, the attachment mechanism 80 holding the respective edge 40 in engagement with or at least abutting the respective attachment portion 82 of the respective payload 30 of the pair of payloads 30. The flexible cantilever 32 has been flexed into its biased state, thus establishing a pre-load force or strain energy in the flexible cantilever 32 suitable for deploying the at least one payload 30. The force provided by this preload is typically provided by a complex release mechanism (e.g., attachment/release mechanism 106).

In fig. 8, the link 92 has been released, releasing the attachment mechanism 84. The attachment portion 82 of the payload 30a is disconnected from the corresponding edge 40 of the port 26a, at which edge 40 the attachment portion 82 is attached. The release of the attachment 82 releases the flexing of the flexible cantilever 32 to release the stored strain energy. The transition of the flexible cantilever 32 from the biased position to the default position enables the payload 30a to move outwardly away from the attachment hub 14. Deployment of the payload 30a from the attachment hub 14 may be achieved by using the cantilever 32 and completely eliminate the need for expensive and complex attachment mechanisms at the port 26 a.

In fig. 9, the complex attachment mechanism 106 has been actuated, thereby deploying payload 30b outwardly away from port 26 b. The satellite 12 is completely disconnected from the attachment hub 14 and is in a free operating mode disconnected from the attachment hub 14. In fig. 10, the satellite 12 is shown detached from the attachment hub 14. During handling and use of the satellite 12 separate from the attachment hub 14, the payloads 30a and 30b are held apart from each other by the cantilever 32.

In summary, the satellite 12 has a number of benefits over conventional satellites 12. The use of a flexible cantilever 32 is sufficient to meet the rigidity requirements of the track operation and also to meet the loading at the ESPA attachment hub 14. The effect of the curved cantilever 32 on the force at the ESPA interface port 26 is negligible. The preload of the curved boom 32 allows one payload 30 of a pair of payloads 30 to be quickly deployed from the attachment hub 14, thereby eliminating the need to provide two complex attachment mechanisms 106 to deploy the satellite 12. This elimination reduces the overall cost, number of parts, and complexity of attaching the satellite 12 to the attachment hub 14. The flexible cantilevers 32 do not complicate attachment (e.g., manual attachment) of the payload 30a to the port 26a because the deflection required to establish a preload and engage the respective attachment portion 82 with the respective port 26 can be minimized. Greater utility of the task may be achieved by providing continuous connections between payloads 30 and eliminating the need for expanded payloads 30 to fit within each other. Further, as shown in fig. 11-14, the concepts of the present invention may be extended to include additional payloads 30, such as using additional flexible cantilevers 32.

Referring now in part to fig. 11 and 12, the present disclosure includes a design method for a satellite 12 having at least one payload 30 of payloads 30 passively deployed from a respective attachment hub 14. As previously mentioned, the depicted satellite 12 is configured to meet the stiffness requirements of a satellite attached to and carried by the attachment hub 14 during launch or travel to a release environment, while also providing a freely detached satellite of sufficient stiffness to be able to be maneuvered into motion independently of the attachment hub 14 in the release environment.

In the schematic diagrams of fig. 11 and 12, two payloads are identified as payload 30_αAnd a payload 30_β. Payload 30_αAttached to attachment hub 14 by non-complex attachment mechanism 84, and payload 30_αAttached to the attachment hub 14 by a complex attachment mechanism 106. FIG. 11 depicts the free, separated or unfolded state of a satellite 12 as a two-mass-one-spring systemState. Fig. 12 depicts the stowed or attached state of the satellite 12 as a two-mass three-spring system, with two additional springs being the attachment mechanisms 84 and 106.

The unfolding system of FIG. 11 has a natural frequency, which can be represented by equation 1, where ω is_nIs the natural frequency, K₃₂Is the spring constant, m, of the cantilever 32_αAnd m_βRepresenting payload 30 of a coupled pair of payloads 30_αAnd 30_βThe quality of (c). With respect to equation 1, in certain embodiments, payload 30_αAnd 30_βCan be considered equal.

Equation 1:

the loading system of FIG. 12 has a second and higher frequency ω₂And is represented by the following equations 2 and 3. Again, in such an equation, in some embodiments, the payload 30 may be assumed to be_αAnd 30_βAre equal in mass, so m can represent m_αOr m_β. In some embodiments, at least for equations 2 and 3, the spring element constant K of the uncomplicated attachment mechanism 84 can be assumed₈₄And the spring constant K of the complex attachment mechanism 106₁₀₆Are equal, and K represents K₈₄Or K₁₀₆。

Equation 2:

equation 3:

in addition, in the stowed state of the satellite 12, and therefore with the cantilever 32 in its biased state, the stiffness of the cantilever 32 is derived from the target natural frequency by equation 4. Preload force F of boom 32_PLRepresented by equation 5, the preload force is used to load the payload after releasing the attachment mechanism 84One of the charges 30 is passively released from the attachment hub 14. In equation 5, Δ R_αIs the distance each payload 30 deflects outward from the attachment hub 14 when the preload force is released.

Equation 4:

equation 5:

F_PL＝K₃₂ΔR_α

with respect to equations 1 through 5 provided above, the relevant dimensions and characteristics of the three satellite embodiments are provided in table 1 below. For example, different embodiments represent aspects of the satellite 12, which satellite 12 may be used with different attachment hubs having different diameters and numbers of ports 26 (i.e., different circumferential spacings between the ports 26).

Table 1:

whereas the flexing of the satellite 12 can allow the satellite 12 to be attached to the attachment hub 14, the satellite 12 will apply a torque to at least one respective port 26, with a respective payload 30 attached to these ports 26. Applying no torque or assuming K at the supposedly complex attachment mechanism 106₁₀₆With infinite rigidity, the exemplary cantilever 32 will be in contact with the attachment mechanism 84 and payload 30_αA torque is applied to the attached edge 40.

In the example of embodiment 3 of table 1 (with the additional assumption of K)₈₄≠K₁₀₆) The torque on each edge 40 attached with the attachment mechanism 84 ranges from about 5Nm to about 35Nm, or from about 10Nm to about 30Nm, or from about 20Nm to about 25Nm (e.g., about 21 Nm).

In the same modified example of embodiment 3 of table 1, where the torque capacity specified at the edge 40 of the annular ESPA attachment hub 14 is about 1.2x10³Nm, the torque applied by the flexible cantilever 32 may be equal to or less than about 1% to about 5% of the allowable torque at the rim 40 by specification (via specification). For example, a torqueThe torque may be in the range of about 1.5% to about 3% of the allowable torque, or about 1.7% of the allowable torque capacity.

Referring to fig. 13-16, another exemplary satellite 112 is shown. The satellite 112 uses the same reference numerals as used to refer to the satellite 12, but prefixed by 100 to each reference numeral. Additionally, the foregoing description of satellite 12 applies equally to satellite 112, except as described below. Further, it will be appreciated upon reading and understanding the specification that aspects of satellite 12 and satellite 112 may be used in place of or in combination with each other, where applicable.

Referring first to fig. 13, a satellite 112 is shown attached to an attachment hub 114. The satellite 112 includes a plurality of payloads 130 and a plurality of flexible cantilevers 132. A satellite 112 according to the invention may comprise two initial payloads 130 coupled to each other by a flexible boom 132, further comprising a further payload 130, which further payload 130 may for example be connected in series with the initial payload 130, and may for example be attached to the initial payload 130 by an additional flexible boom 132.

The depicted satellite 112 includes three payloads 130, with adjacent payloads 130 coupled to each other (e.g., in series) by a flexible cantilever 132. Although each payload 130 is depicted as having the same volume, in some embodiments their volumes may be different. Also, although the plurality of flexible cantilevers 132 are depicted as being identical to one another, in other embodiments, the cantilevers 132 may differ in any one or more of shape, size, length, or ratio.

In fig. 13-15, satellite 112 is attached to attachment hub 114. Two uncomplicated attachment mechanisms 184 and one attachment mechanism 206 hold the respective edge 140 in engagement with, or at least in abutment with, the respective attachment portion 182 of the respective payload 130. The flexible cantilevers 132 have deflected to their respective biased states. Attachment mechanism 184 is used to disconnect outer payloads 130a and 130c from attachment hub 114.

To deploy satellites 112 from attachment hubs 114, attachment mechanisms 180 are sequentially released in sequence, with attachment mechanisms 184 at ports 126a and 126c, respectively, being released before attachment mechanism 206 at port 126b is released. The attachment mechanisms 184 may be released simultaneously, or one of the attachment mechanisms 184 may be released before the other attachment mechanism 184 is released.

For example, after the connectors of the two attachment mechanisms 184 (the same as the connectors 92 of fig. 5) are released, thereby releasing the attachment mechanisms 184, the attachment portions 182 of the payloads 130a and 130c will be disconnected from the respective edges 140 of the ports 126a and 126c, with the attachment portions 182 attached to the ports 126a and 126 c. The release of the attachment 182 enables the flexible cantilever 132 to unflex and release the stored strain energy. The transition of flexible cantilever 132 from the biased position to the default position causes payloads 130a and 130c to move outward away from attachment hub 114. Deployment of payloads 130a and 130c from attachment hub 114 may be accomplished through the use of cantilever arms 132, thus completely eliminating the need for expensive and complex attachment mechanisms at ports 126a and 126 c.

In fig. 16, complex attachment mechanism 206 (fig. 15) has also been actuated, thus allowing payload 130b to deploy outward away from port 126 b. Satellite 112 is completely decoupled from attachment hub 114. During handling and use of satellite 112, payload 130a, 130b, and 130c are spaced apart from one another by boom 132.

In some embodiments, attachment mechanism 184 may be used to disconnect intermediate payload 130b, and conversely, a complex attachment mechanism may be used to deploy one of payload 130a or payload 130 c. In other embodiments, only one of payload 130a or payload 130c may be disconnected from attachment hub 114 via uncomplicated attachment mechanism 184, while the other two of payloads 130 are deployed via complex attachment mechanism 206.

With continuing reference to figures 13-16 and with further reference to figures 7-10, the present invention includes a method of deploying a satellite 12, 112 from an attachment hub 14, 114. The method comprises the following steps: (a) providing a satellite 12, 112 having a pair of payloads 30, 130 with a cantilever 32, 132 extending therebetween, and each payload 30, 130 coupled to an attachment hub 14, 114; (b) releasing the attachment of one of the payloads 30, 130 to the attachment hub 14, 114; and (c) transitioning the flexible cantilevers 32, 132 from the biased state having the stored strain energy to a default state, whereby release of the stored strain energy by the flexible cantilevers 32, 132 causes one of the payloads 30, 130 to deploy outward from the attachment hub 14, 114. The method can comprise the following steps: releasing the stored strain energy from the flexible cantilever 32, 132 includes changing the cantilever 32, 132 from a deflected state in a biased state to an undeflected state. The method may further comprise the steps of: (d) the attachment mechanism 84, 184 is released, which selectively couples the payload 30, 130 to the attachment hub 14, 114 without having to apply a force to the payload 30, 130 that would cause the payload 30, 130 to deploy outward from the attachment hub 14, 114.

In summary, with reference to each of the embodiments described above, the present disclosure provides an exemplary satellite 12, 112 comprising: a pair of payloads 30, 130 coupled to each other by flexible cantilevers 32, 132. Wherein the flexible cantilever arms 32, 132 are configured to facilitate manual engagement of a pair of payloads 30, 130 with an associated attachment hub 14, 114 and also provide a passive release force for deploying at least one payload 30, 130 in an outward direction toward the attachment hub 14. When the flexible cantilevers 32, 132 flex to attach the payload 30, 130 to the attachment hub 14, 114, the strain energy stored in the flexible cantilevers 32, 132 will act as potential energy for achieving passive release. When at least one payload 30, 130 is released from the attachment hub 14, 114, the strain energy will be released, which can be done by a non-complex, non-unusual attachment mechanism 84, 184. An additional payload 30, 130 may be attached in series with the pair of payloads 30, 130, with a flexible cantilever for attaching adjacent payloads 30, 130. These payloads 30, 130 may be released from attachment hubs 14, 114 via attachment mechanisms 84, 184 or through complex attachment mechanisms 106, 206.

Although the invention has been shown and described with respect to one or more certain preferred embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings. In particular and unless otherwise indicated, various functions performed in relation to the above described elements (components, assemblies, stores, compositions, etc.), the terms (including a reference to a "means") used to describe such elements are intended to correspond, even though not structurally equivalent to the disclosed structure which performs the function in the herein illustrated exemplary embodiment or embodiments of the invention. In addition, while a particular feature of the invention may have been described above with respect to only one or more of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application.