Articulated inlets for air-breathing long-range projectiles and missiles

Abstract

The projectile includes a wing structure that forms both an inlet for intake of combustion air for the projectile's propulsion system during initial flight range and a lifting surface for the projectile after the propulsion system's thrusters have burned out. The wing structure functions as both an inlet and a lifting surface, enabling both long-range flight of the projectile to its target and optimal flight time. The wing structure includes at least one wing that is movable from a folded position in which the wing extends along the body section of the projectile and defines an inlet, to a deployed position in which the wing extends outward from the body section and forms a lifting surface. Any number of wings may be provided, and the wings may be deployed simultaneously or sequentially, depending on the application.

Description

[Technical field]

[0001] The present disclosure relates to inlets for projectiles and missiles. [Background technology]

[0002] Projectiles such as missiles are typically space constrained and require balancing of space for both guidance electronics and propulsion systems. In an exemplary ramjet-type projectile, a solid fuel ramjet propulsion system using airflow ducts can cause a significant space shortage within the projectile. Due to the volumetric limitations of the standard space provided within the projectile, shared by the ramjet propulsion system, seeker hardware and processor electronics, and warhead, the projectile may be configured with a propulsion system that increases the flight range to the target for the initial flight phase. However, conventional projectiles may fall short in maximizing range, which depends on either reducing drag in and around the inlet or increasing lift on the projectile's airframe.

[0003] One previous attempt to increase the range of a projectile to a target involves increasing the thrust of the ramjet, however this solution is flawed in that it does not address the source of drag created by the inlet of the air-breathing propulsion system after the ramjet fuel is consumed, which can result in poor projectile performance. Summary of the Invention

[0004] The present application provides a projectile that uses a wing structure to form both an inlet for intake of combustion air for the projectile's propulsion system during the initial flight range, and a lifting surface for the projectile after the propulsion system's thrusters have burned out. In contrast to conventional projectiles, which include ramjet-only variants that provide optimal flight time to the target but short range, and wing-only variants that provide long range but undesirably long flight times, the wing structure acting as both an inlet and a lifting surface allows for both long range and optimal flight time to the target.

[0005] The wing structure includes at least one wing movable from a folded position in which the wing extends along the thrust section of the projectile and defines an inlet, to a deployed position in which the wing extends outwardly from the thrust section to form a lift surface. Any number of wings may be provided, and the wings may be deployed simultaneously or sequentially depending on the application.

[0006] The propellant section of the projectile may include a recess that is covered by the wing when the wing is in a folded position such that an inlet is defined between the propellant section and the wing, and when the wing moves away from the propellant section, the recess is exposed or opens such that the inlet is open.

[0007] The wing may be actuated by any suitable actuator and rotated away from the propellant section to the deployed position. The wing may be configured for single or multiple axis rotation, where the wing pivots about a point of attachment to the propellant section and also rotates about its axis. The wing may be formed by two wings that engage with each other to define an inlet and disengage from each other when the wings move from the folded position to the deployed position.

[0008] According to one aspect of the disclosure, a projectile includes at least one wing that functions both as an air inlet during propulsion and as a lifting surface after propulsion.

[0009] According to one aspect of the disclosure, the projectile may include at least one wing that closes the inlet when in a folded position and opens the inlet when in a deployed position.

[0010] According to one aspect of the disclosure, a projectile may have a ramjet and an inlet that forms a lifting surface after an initial propulsion stage of the ramjet.

[0011] According to one aspect of the disclosure, the projectile may include at least one wing configured to rotate on two axes as the wing moves from a position where the wing acts as an inlet to a position where the wing forms a lifting surface.

[0012] According to one aspect of the disclosure, a projectile may include at least one wing that is oriented in the same plane when the wing is in a position to act as an inlet and when the wing is in a position to form a lifting surface.

[0013] According to one aspect of the disclosure, the projectile may include at least one wing formed by two wings engageable to define an inlet and disengageable to open the inlet and form a lift surface.

[0014] According to one aspect of the disclosure, the projectile may include a number of wings arranged symmetrically about the projectile and functioning as air inlets during propulsion and lifting surfaces after propulsion.

[0015] According to one aspect of the disclosure, a projectile includes a body section and at least one wing movable between a folded position that extends along the body section during an initial flight range of the projectile and defines an inlet, and a deployed position that extends outwardly from the body section after the initial flight range to form a lifting surface for the projectile.

[0016] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may be formed as an inlet wall that closes the inlet when in the folded position and opens the inlet when in the deployed position.

[0017] According to an embodiment of any paragraph or paragraphs of this Summary, the propellant body portion may include an outer circumferential surface having a recess covered by the at least one wing to define the inlet.

[0018] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may be configured to rotate relative to the propulsion body portion from the folded position to the deployed position.

[0019] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may be configured for biaxial rotation.

[0020] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may be configured to rotate in a first plane of rotation to a first deployed position and thereafter to rotate in a second plane of rotation perpendicular to the first plane of rotation to a second deployed position.

[0021] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may be configured to pivot about an attachment point and rotate about an axis of the at least one wing.

[0022] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may include a first wing portion and a second wing portion engageable to form the inlet and disengageable by rotating in opposite rotational directions from the folded position to the deployed position to form two lift surfaces.

[0023] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may be configured to pivot at least 90 degrees about a point of attachment to the propellant body portion.

[0024] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing that is pivotable in the same plane may be oriented in the same plane when in the folded and deployed positions.

[0025] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may be attached to the projectile at an attachment point to the propellant section aft of the inlet.

[0026] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may extend vertically from the propulsion body portion when in the deployed position.

[0027] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may include two or more wings defining two or more inlets between the propellant body portion.

[0028] According to an embodiment of any paragraph or paragraphs of this Summary, the two or more inlets may be symmetrically arranged around the propellant body portion.

[0029] According to an embodiment of any paragraph or paragraphs of this Summary, the two or more inlets may be part of an annular inlet.

[0030] According to an embodiment of any paragraph or paragraphs of this summary, the projectile is a solid fuel ramjet, a liquid fuel ramjet, or a ducted rocket.

[0031] According to an embodiment of any paragraph or paragraphs of this Summary, the projectile may further include at least one of an electric motor, a mechanical actuator, a pneumatic actuator, a hydraulic actuator, or an energetic material configured to deploy the wings from the folded position.

[0032] According to another aspect of the present disclosure, a ramjet includes a propulsion body section including a propulsion engine for the ramjet, and at least one wing movable between a folded position in which the at least one wing extends along the propulsion body section during an initial range of flight of a projectile to define an inlet for intake of combustion air for a propulsion system, and a deployed position in which the at least one wing extends outwardly from the propulsion body section to form a lifting surface for the projectile after a propulsion engine has burned out.

[0033] According to an embodiment of any paragraph or paragraphs of this Summary, the at least one wing may be configured to rotate from a folded position covering a recess formed in an outer periphery of the propellant body portion to a deployed position in which it is removed from the recess and opens the inlet.

[0034] According to yet another aspect of the present disclosure, a method of operating a projectile includes firing a propulsion engine in a propellant section of the projectile during an initial flight range of the projectile; drawing in air through an inlet defined by at least one wing disposed in a folded position relative to the propellant section for firing in the propulsion engine during the initial flight range; deploying the at least one wing from the folded position to a deployed position extending outward from the propellant section after the propulsion engine is burned out during a subsequent flight range relative to the initial flight range; and generating lift for the projectile via the at least one wing in the deployed position.

[0035] To the accomplishment of the foregoing and related ends, the present disclosure 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 disclosure. These embodiments are indicative, however, of but a few of the various ways in which the principles of the disclosure may be employed. Other objects, advantages and novel features of the invention will become apparent from the following detailed description taken in conjunction with the accompanying drawings. [Brief description of the drawings]

[0036] The accompanying drawings, which are not necessarily to scale, depict various aspects of the present disclosure. [Figure 1] 1 shows a schematic diagram of a projectile having a propulsion system. [Diagram 2] 2 shows the projectile of FIG. 1 during an initial range of flight with the projectile's wings in a folded position and defining an inlet. [Diagram 3] 3 shows the projectile of FIG. 2 during a subsequent flight span in which the projectile's wings are deployed to form lifting surfaces. [Figure 4] 2 illustrates a wing of the projectile of FIG. 1 according to an illustrative embodiment configured to rotate on two axes to move the wing from a folded position to a deployed position. [Diagram 5] 5 shows the wing of FIG. 4 in the deployed position. [Figure 6] 10 illustrates a wing of the projectile of FIG. 1 according to another exemplary embodiment, wherein the wing is configured to rotate on a single axis to move from a folded position to a deployed position. [Figure 7] 7 shows the wing of FIG. 6 in the deployed position. [Figure 8] 10 illustrates a wing of the projectile of FIG. 1 according to yet another exemplary embodiment formed by two wings engaging with each other to define an inlet when the wings are in a folded position. [Figure 9] 9 shows the wing of FIG. 8 in a deployed position in which the wing forms two lifting surfaces. [Figure 10] 10 shows a flow chart illustrating a method of operating a projectile such as the projectile shown in any of FIGS. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0037] The principles described herein find application for use with projectiles such as artillery shells and missiles. The projectiles may be implemented in a variety of applications, such as any other suitable projectile application, including defense or non-military applications. The principles described herein may be implemented with any suitable projectile, such as a solid fuel ramjet, liquid fuel ramjet, or ducted rocket. Projectile launch systems, such as tube or gun launch systems, may also be used in conjunction with the projectiles and principles described herein.

[0038] Referring first to FIG. 1, a schematic diagram of a projectile 20 is shown. The projectile 20 may be a solid fuel ramjet, a liquid fuel ramjet, a ducted rocket, or any other suitable projectile. For example, the projectile 20 may be a ramjet that includes a propulsion body section 22 having a propulsion system and engine for the ramjet. The propulsion body section 22 houses various components of the propulsion engine. A diffuser 24 may be disposed in the propulsion body section 22, and an air inlet 26 may be defined between the diffuser 24 and the propulsion body section 22. A combustion chamber 28 is disposed downstream of the inlet 26, and a nozzle 30 is disposed downstream of the combustion chamber 28.

[0039] During operation, the inlet 26 is configured to draw in ambient air and compress the air during the forward movement of the projectile 20. The propulsion engine of the ramjet projectile 20 utilizes the forward motion of the projectile 20 to compress and combust the incoming combustion air without the use of a rotary compressor. A combustion chamber 28 is fluidly connected to the inlet 26 to receive the compressed air. In the combustion chamber 28, fuel is added and combusted to heat the compressed air. In the nozzle 30, the density of the air is reduced and the acceleration of the heated air is increased, generating thrust for the projectile 20.

[0040] During the initial launch of the projectile 20, the inlet 26 may be in a closed position during the initial launch to reduce drag before the projectile 20 propels. The projectile 20 may be launched from a gun or other suitable launch system. After the projectile 20 leaves the gun, the inlet 26 may be actuated open during the initial flight range of the projectile 20. During the initial flight range, the inlet 26 draws in combustion air due to the forward motion of the projectile 20 such that the initial flight range is the propulsion phase of the ramjet projectile 20. As shown in FIG. 1, the inlet 26 is defined by at least one wing 34 having a folded position in which the wing 34 extends along the propellant section 22 during the initial flight range of the projectile 20.

[0041] With additional reference to Figures 2 and 3, further details of the wing 34 are shown. Figure 2 shows the projectile 20 during an initial flight range with the wing 34 in a folded position and forming the inlet 26 shown in Figure 1. As shown in Figure 3, after the propulsion engines burn out and the initial flight range is completed, the wing 34 is movable from the folded position shown in Figure 2 to a deployed position extending outward from the propulsion body section 22. An attachment point 35 at which the wing 34 is attached to the projectile 20 may be aft of the inlet 26 relative to the forward end 36 of the projectile. The attachment point 35 is formed at a fixed position along the propulsion body section 22. The wing 34 is configured to rotate about the attachment point 35 from the folded position to the deployed position. For example, the wing 34 may pivot about the attachment point 35. When in the deployed position, the wing 34 forms a lifting surface to generate lift for the projectile 20 after the initial flight range. In this manner, the inlet 26 that previously created drag for the projectile 20 is eliminated, creating lift and further increasing the flight range of the projectile 20.

[0042] The wings 34 function as both an inlet for the projectile 20 during the initial propulsion phase and as a lifting surface during flight of the projectile 20 after the propulsion phase. In contrast, a conventional projectile may be a wing-only variant or a ramjet-only variant. In a wing-only variant, the projectile has lifting wings without an inlet configured to take in air during propulsion. In a ramjet-only variant, the projectile has an inlet without any lifting surface to extend the flight range of the projectile after the propulsion phase.

[0043] A wing-only variant may provide longer range but also provide an undesirably long flight time to the target, while a ramjet-only variant may provide optimal flight time to the target but also provide an undesirably short range to the target, resulting in the deficiencies of both variants. By using the wings 34 which function as both air inlets and lifting surfaces, the advantages of both variants are obtained in a single projectile in that the wings 34 enable both long range and optimal flight time to the target for the projectile 20.

[0044] The wings 34 are formed as inlet walls that close the inlets 26 when in the folded position so that the inlets 26 are unavailable for air intake for propulsion, and that expose or open the inlets 26 away from the body section when in the deployed position. As shown in Figure 3, the outer peripheral surface 37 of the body section 22 is formed with recesses 38 that are covered by the wings 34 to form the inlets 26 when the wings 34 are in the folded position. Thus, the inlets 26 are defined between the body section 22 and the wings 34.

[0045] The recess 38 may have any suitable shape and extend parallel to the longitudinal axis L of the projectile section 22. The wings 34 also extend parallel to the longitudinal axis L when in the folded position. For example, the recess 38 may have a shallow depth and be elongated along the length of the projectile section 22. The length of the recess 38 may depend on the desired size of the inlet 26 based on the operational characteristics of the projectile 20. The inlet 26 may have any suitable shape, such as annular.

[0046] The wings 34 may have any suitable shape and length. The wings 34 may extend along more than half or most of the length of the propellant section 22. The length of the wings 34 may depend on the desired length of the inlet 26. The wings 34 may be shaped to have a planar body with a small thickness and a large length. The planar surface 39 of the wings 34 may be shaped to allow the wings 34 to mate with the outer circumferential surface 37 of the propellant section 22 when the wings 34 are engaged with the outer circumferential surface 37 and cover the recess 38.

[0047] The outer periphery 37 and the flat surface 39 of the wings 34 may be formed to have complementary shapes such that the wings 34 mate with the outer periphery 37 when in the folded position. The flat surface 39 may have a tapered shape that tapers from the attachment point 35 on the propellant section 22 to the opposite end of the wings 34. When in the deployed position, the wings 34 may extend perpendicular or transverse to the longitudinal axis L defined by the propellant section 22. The wings 34 may have many other shapes.

[0048] As shown generally in FIG. 3, the projectile 20 includes an actuator 40 disposed within the propellant section 22 and configured to deploy the wings 34 from a folded position to a deployed position. Any suitable actuator may be used. Exemplary actuators may include electric motors, mechanical actuators, pneumatic actuators, hydraulic actuators, or energetic materials. The actuator 40 may include any suitable pistons, cylinders, pumps, motors, valves, and the like. Actuation of the wings 34 occurs after the propulsion engines have burned out and the initial flight range of the projectile 20 has ended, such that lift of the projectile 20 is desired to extend the range.

[0049] Any number of wings 34 and inlets 26 may be provided. More than one wing 34 may be provided. Each wing 34 may correspond to a single inlet 26 formed between the corresponding wing 34 and the propellant section 22 such that the projectile 20 includes multiple inlets 26. Each wing 34 may share an actuator 40 or have a unique actuator such that the wings 34 can be deployed simultaneously or sequentially. The sequence of actuation of the wings 34 may depend on the application and the desired lifting and lowering motion. The wings 34 may be symmetrically spaced about a common circumference of the propellant section 22. Other arrangements of the wings 34 may also be appropriate depending on the application. As shown in FIG. 3, in an exemplary embodiment, the projectile 20 may include two wings 34 forming two inlets 26 diametrically opposed to one another. In an exemplary embodiment, the two or more inlets may be part of an annular inlet of the projectile 20.

[0050] 4-9, one or more wings 34 may rotate when moving from a folded position to a deployed position. The rotation of the wings 34 may include pivoting. Each wing 34 may be rotatable or pivotable through an angle of at least 90 degrees. Depending on the application and the final deployed position of the wings 34, a smaller or larger angle of rotation or pivoting may be appropriate. As shown in FIGS. 4 and 5, in a first exemplary embodiment of the projectile 20a, the wings 34 may be configured for biaxial rotation from the folded position 34a to the deployed position 34b. During deployment of the wings 34, the wings 34 have a first range of rotation θ in a first plane of rotation and a second range of rotation α occurring in a second plane of rotation perpendicular to the first plane of rotation in which the first range of rotation θ occurs.

[0051] For example, the wing 34 can pivot about 90 degrees about an attachment point 35 away from the propellant section 22 during the first range of rotation θ such that the wing 34 pivots to extend perpendicular to the propellant section 22 in the first deployed position 34b. The attachment point 35 may include any suitable hinge mechanism, joint, or other linkage that attaches to the propellant section 22. In an exemplary embodiment, a two-axis hinge mechanism may be suitable. The attachment point 35 may include any suitable component, such as a ball bearing, spring, leaf, pin, tube, clip, or the like. The wing 34 may rotate more or less than 90 degrees during the first range of rotation θ.

[0052] The wing 34 also rotates in a second range of rotation α, which may occur subsequent to the first range of rotation θ. For example, the wing 34 may rotate approximately 90 degrees from a first deployed position 34b shown in FIG. 4, which may be an initial deployed position, to a second deployed position 34c shown in FIG. 5, which may be a final deployed position. The wing 34 may rotate about its own axis during the second range of rotation α. ​​In the second or final deployed position 34c, the plane of the wing 34 may extend in a plane parallel to the plane of rotation of the first range of rotation θ. Two or more wings may be provided that undergo the same biaxial rotational deployment shown in FIGS. 4 and 5. Two or more wings may be deployed simultaneously or sequentially.

[0053] In an alternative embodiment, the wing 34 may rotate about its own axis during a first range of rotation θ so that when in the first deployed position 34b, it extends parallel to the propellant section 22. The wing 34 may then pivot outwardly from the propellant section 22 to the second deployed position 34b shown in FIG. 5 during a second range of rotation α. ​​In yet another exemplary embodiment, the wing 34 may be configured to rotate about its axis while pivoting about the attachment point 35. In yet another exemplary embodiment, the wing 34 may be configured for multi-axis deployment, where the wing 34 may rotate or pivot about three or more different axes. The rotation of the wing 34 may depend on the desired lift profile of the projectile 20a.

[0054] As shown in Figures 6 and 7, in another exemplary embodiment of the projectile 20b, the wing 34 may be configured for single-axis rotation resulting in only one rotation range θ. The wing 34 may pivot about the attachment point 35 from a folded position 34a shown in Figure 6 to a deployed position 34b shown in Figure 7, which may be the final deployed position of the wing 34. The wing 34 may pivot at least 90 degrees, but the wing 34 may pivot more than or less than 90 degrees depending on the application. The plane of the wing 34 may extend in the plane of rotation of the rotation range θ. Assuming that the wing 34 rotates in a single axis, the wing 34 is oriented in the same plane in both the folded position 34a and the deployed position 34b. This plane is coplanar with the plane of rotation of the wing 34. Two or more wings may be provided that undergo the same deployment motion as shown in Figures 6 and 7.

[0055] As shown in Figures 8 and 9, in yet another exemplary embodiment of the projectile 20c, the wing 34 may be formed by a first wing section 42 and a second wing section 44. The wings 42, 44 are engageable with one another to close or form the inlet 26 (shown in Figure 1) when the wings 34 are in the folded position 34a shown in Figure 8. After an initial flight range or propulsion stage of the projectile 20c, each of the wings 42, 44 may have a single range of rotation θ. During the single range of rotation θ, the wings 42, 44 rotate in counter-rotational directions to disengage and open the inlet 26 when moving from the folded position 34a shown in Figure 8 to the deployed position 34b shown in Figure 9.

[0056] Each of the wings 42, 44 may rotate at least 90 degrees, or more than 90 degrees, or less, depending on the application. The plane 39 of each of the wings 42, 44 may extend in a plane of rotation of a rotation range θ such that the wings 42, 44 are oriented in the same plane in both the folded position 34a and the deployed position 34b. Each wing 42, 44 may have a separate attachment point 35a, 35b and a separate hinge mechanism. Alternatively, the wings 42, 44 may share an attachment point and a hinge mechanism. Two or more wings may be provided that undergo the same deployment action as shown in Figures 8 and 9. As shown in Figure 9, each wing 34 may be formed by two engageable wings 42, 44. In other exemplary embodiments, the wings 42, 44 may also be configured to rotate in two or more axes, as shown in Figures 4 and 5.

[0057] Referring now to FIG. 10, a method 50 for operating a projectile is shown. The method 50 may be used to operate the projectile 20, 20a, 20b, 20c shown in any of FIGS. 1-9. A first step 52 of the method 50 includes firing a propulsion engine in a propulsion system of the propellant portion 22 of the projectile 20, 20a, 20b, 20c during an initial flight range of the projectile 20, 20a, 20b, 20c. A step 54 of the method 50 includes drawing air through an inlet 26 formed between the propellant portion 22 and at least one wing 34 disposed in a folded position relative to the propellant portion 22 for firing in the propulsion engine during the initial flight range.

[0058] A step 56 of the method 50 includes deploying the wings 34 from a folded position to a deployed position in which the wings 34 extend outwardly from the propulsion body section 22 to open the inlet 26, after the propulsion engines have burned out during a subsequent flight range to the initial flight range. The wings 34 may be deployed as shown in any of Figures 4-9. A step 58 of the method 50 includes generating lift for the projectile 20, 20a, 20b, 20c via at least one wing 34 in the deployed position.

[0059] The use of wings as both an inlet and a lifting surface is advantageous in that the projectile configuration maintains the benefits of an airbreathing propulsion system to minimize flight time, while the wings become the lifting surface of the vehicle, thereby extending range using the existing inlet surface area. In an exemplary application, a projectile using the dual-function wings described herein may have a maximum range of about 160 kilometers and a speed of Mach 1.8. In contrast, a wing-only projectile variant has a maximum range of about 140 kilometers and a speed of Mach 0.4, and a ramjet-only projectile variant has a maximum range of about 120 kilometers and a speed of Mach 2.0. Thus, the projectile according to the present application has an improved target range and optimal flight time.

[0060] Although the present disclosure shows and describes certain preferred embodiment(s), it will be apparent to those skilled in the art that equivalent changes and modifications can be made upon reading and understanding the present specification and the accompanying drawings. In particular, with respect to the various functions realized by each of the above-mentioned components (external parts, assemblies, devices, components, etc.), the terms used to describe these elements (including references to "means") are intended to correspond to elements that realize the particular functions of the described elements (i.e., functionally equivalent) but are not structurally equivalent to the disclosed structures that realize the functions in the exemplary embodiments or embodiments of the present disclosure described herein, unless otherwise expressly stated. Also, while a particular feature of the present disclosure may be disclosed above with respect to only one or more of the several described embodiments, such a feature may be combined with one or more other features of other embodiments as desired and advantageous for any given or specific application.

Claims

1. A projectile, A propellant portion; at least one wing, a folded position during an initial range of flight of the projectile, wherein the at least one wing extends along the propellant section to define an inlet; and a deployed position, after the initial flight range, in which the at least one wing extends outwardly from the propellant section to form a lifting surface for the projectile; and At least one wing movable between Including, the at least one wing is configured to rotate relative to the propulsion body from the folded position to the deployed position; The at least one blade is configured for biaxial rotation. Projectile.

2. the at least one wing is formed as an inlet wall; When in the folded position, closing the inlet; and When in the deployed position, opening the inlet.

2. The projectile of claim 1.

3. The propellant portion includes an outer circumferential surface, the outer circumferential surface is covered by the at least one wing and has a recess that defines the inlet; 3. A projectile according to claim 1 or 2.

4. The at least one wing comprises: rotate in a first plane of rotation to a first deployed position; and thereafter rotating in a second plane of rotation perpendicular to the first plane of rotation to a second deployed position. The projectile of claim 1 , configured as follows:

5. The at least one wing comprises: pivoting about an attachment point and rotating about the axis of said at least one wing; The projectile of claim 1 , configured as follows:

6. the at least one wing includes a first wing portion and a second wing portion; The first wing portion and the second wing portion are engageable to form the inlet; and disengageable to form two lift surfaces by rotating in opposite rotational directions from the folded position to the deployed position.

2. The projectile of claim 1.

7. the at least one wing is configured to pivot at least 90 degrees about a point of attachment to the propellant body; A projectile according to any one of claims 1 to 6.

8. the at least one wing is oriented in the same plane when in the folded position and the deployed position; the at least one wing is pivotable within the same plane; 8. The projectile of claim 7.

9. the at least one wing is attached to the projectile at an attachment point to the propellant section aft of the inlet; A projectile according to any one of claims 1 to 8.

10. The at least one wing comprises: the at least one wing extends perpendicularly from the propellant body when in the deployed position; A projectile according to any one of claims 1 to 9.

11. the at least one wing comprises two or more wings; defining two or more inlets between the two or more wings and the propellant body portion; A projectile according to any one of claims 1 to 10.

12. The two or more inlets are arranged symmetrically around the propellant body.

12. The projectile of claim 11.

13. The two or more inlets are part of an annular inlet.

13. A projectile according to claim 11 or 12.

14. The projectile is a solid fuel ramjet, a liquid fuel ramjet, or a ducted rocket. A projectile according to any one of claims 1 to 13.

15. The projectile further comprises: at least one of an electric motor, a mechanical actuator, a pneumatic actuator, a hydraulic actuator, or an energetic material configured to deploy the wings out of the folded position; A projectile according to any one of claims 1 to 14.

16. A ramjet, a propulsion body section including a propulsion engine for the ramjet; at least one wing, a folded position during an initial range of flight of the projectile, in which the at least one wing extends along the body section to define an inlet for intake of propulsion system combustion air; and a deployed position, after the propulsion engine has burned out, in which the at least one wing extends outwardly from the propulsion body section to form a lifting surface for the projectile; and At least one wing movable between Including, ramjet.

17. The at least one wing comprises: From the folded position, in which the at least one wing covers a recess formed on the outer periphery of the propellant body, to the deployed position, where the at least one wing is removed from the recess to open the inlet; configured to rotate; 17. The ramjet of claim 16.

18. 1. A method of manipulating a projectile, comprising: firing a propulsion engine within a propellant section of the projectile during an initial range of flight of the projectile; inhaling air for combustion in the propulsion engine during the initial flight range through an inlet defined by at least one wing disposed in a folded position relative to the propulsion body section; deploying the at least one wing from the folded position to a deployed position in which the at least one wing extends outwardly from the propulsion body portion after the propulsion engine has burned out during a flight range subsequent to the initial flight range; generating lift for the projectile via the at least one wing in the deployed position; A method comprising:

Images