An ultra-high-speed aircraft fast-throwing fairing and its aerodynamic separation method

Abstract

The application discloses a kind of super-high-speed aircraft fast-throwing fairing and its aerodynamic separation method.For solving the problem that fairing and aircraft main body are difficult to separate under super-high-speed flight state.The device includes movable cover, torsion spring mechanism and wing assembly.The method includes: installing movable cover on both sides of fairing, connecting movable cover and fixed plate, fairing and main body with explosive bolt;Fixing torsion spring mechanism, connecting torsion spring mechanism and wing with bearing and adjusting wing angle of attack;When aircraft flies normally, wing is blocked by movable cover;When fairing is separated, explosive bolt is detonated, the connection between fairing and main body is broken, movable cover is fixed, wing is unfolded by torsion spring mechanism, and fairing obtains aerodynamic force to separate out by wing aerodynamics.The application mainly relies on pyrotechnic device and mechanical structure, which is efficient and reliable, has strong anti-interference ability and low economic cost;By adjusting the angle of bearing and wing design, the demand in different scenarios can be met.

Description

Technical Field

[0001] This invention belongs to the field of fairings, specifically relating to a fast-release fairing for hypersonic aircraft and its aerodynamic separation method. Background Technology

[0002] During flight within the atmosphere, the fairing plays a crucial role in protecting the payload from aerodynamic heating, high-speed airflow, and the effects of acoustic and vibrational environments. When the spacecraft enters a region of thin atmosphere, the fairing must reliably separate from the launch vehicle. The fairing's separation performance directly affects the safety of the payload and the success or failure of the launch mission.

[0003] Currently, existing fairing designs mainly employ a detachable structure, where the fairing is composed of two or more half-fairing segments joined together. After reaching a predetermined altitude, the fairing separates from the main body via an unlocking and separation mechanism. Typical technical solutions are as follows.

[0004] Patent CN115615262B discloses a "Projectile Separation Fairing and its Design Method." This design divides the fairing into a first half and a second half, connected to each other and to the rocket's final stage via radial and axial explosive bolts, respectively. During separation, the explosive bolts detonate to unlock the fairing, and a separation mechanism (composed of an actuator, actuator rod, piston, etc.) located inside the half-fairing pushes the two half-fairings to move radially in opposite directions, achieving projectile separation of the fairing. To cope with the separation impact, the design incorporates embedded parts connected to reinforcing ribs within the shell as mounting load-bearing interfaces for the separation mechanism's base, and a linear guide area at the docking end frame cooperates with a guide rod to constrain the separation trajectory. However, this design is essentially still a split-half-fairing structure. The two half-fairings require structural component layout optimization to achieve centroidal symmetry to ensure consistent separation attitudes. However, actual assembly tolerances and deviations in the force applied by the separation mechanism still make it difficult for the two half-fairings to separate completely synchronously, posing a risk of collision with the payload inside the fairing.

[0005] Patent CN121425537A discloses a "self-separating fairing," which also employs a separable structure consisting of a first half-fairing panel and a second half-fairing panel. A magnetic pre-fixing structure (permanent magnet strips combined with electromagnetic adsorption blocks) is installed at the joint of the two halves to replace the traditional bolt connection. Electromagnetic force is used to achieve a detachable connection between the halves, and a split-type seam mechanism (a nested female seam assembly and a female seam assembly) achieves seam sealing. During separation, the electromagnetic adsorption blocks are de-energized, releasing the magnetic constraint. Simultaneously, a composite drive separation mechanism consisting of a compression torsion spring and a guide push rod, located at the joint, provides ejection thrust, causing the two halves to separate. This design uses a nested seam combined with an elastic sealing skirt to improve the airtightness of the seam. However, this scheme still has shortcomings: First, the magnetic pre-fixing structure relies on the continuous power supply of the electromagnetic adsorption block to maintain the adsorption state. In the low-temperature vacuum environment, the reliability of the electromagnetic system power supply is tested. Once the power supply is abnormal, the pre-fixing of the half-cover will fail. Second, the separation force provided by the compression torsion spring drive method is limited by the pre-compression of the torsion spring, which has limited separation boost capability for large-size fairings. Moreover, the torsion spring is at risk of stress relaxation after long-term pre-compression storage. Furthermore, this scheme still adopts the basic configuration of two half-covers separation, and the joint adopts a combination of mechanical nesting and sealing skirt. Its long-term fatigue resistance and sealing durability under extreme aerodynamic and thermal environments still need further verification.

[0006] In summary, existing fairing designs generally adopt a split assembly structure, which has common problems such as insufficient reliability of joint sealing, difficulty in accurately controlling the consistency of separation attitude, and limited safety or driving force of separation drive method. Summary of the Invention

[0007] This invention proposes a fast-release fairing for hypersonic aircraft and its aerodynamic separation method, solving common problems encountered during the separation of fairings with separable, assembled structures at high speeds, such as insufficient reliability of seam sealing, difficulty in precisely controlling separation attitude consistency, and limitations in the safety or driving force of the separation drive method. This invention achieves stable fastening of components in the unseparated state through fixed components (such as support frames and torsion spring fasteners), unlocks the fixed components from moving parts using explosive bolts, and employs a torsion spring mechanism to achieve wing deployment. While maintaining an integrated fairing design, the aerodynamic changes resulting from wing deployment achieve separation of the fairing from the aircraft body, realizing a low-cost, efficient, and reliable fast-release fairing separation method.

[0008] The technical solution for achieving this invention is as follows: a fast-release fairing for a hypersonic aircraft, comprising a fairing body, a support frame, two torsion spring mechanisms, two wing assemblies, and four movable fairing surfaces; the rear end of the fairing body is connected to the aircraft body via explosive bolts, and two elongated windows are opened on the outer wall of the fairing body; the four movable fairing surfaces are paired together and connected to the elongated windows of the fairing body via hinges, and one group of movable fairing surfaces can be opened and closed outwards via hinges; two bosses are provided inside the fairing body, and the bosses and the support frame are fixed to the inner wall of the fairing body, with the bosses close to the front end face of the movable fairing surfaces, and the bosses and the support frame are used to connect the fairing body and the torsion spring mechanism; a wing assembly is provided between one group of movable fairing surfaces, and the torsion spring mechanism is connected to the wing assembly via bearings.

[0009] A method for aerodynamic separation of a fast-slinging fairing from a hypersonic vehicle includes the following steps:

[0010] Step 1: Detonate the explosive bolts to unlock the fairing body from the aircraft body, unlock the fixed plate, and separate it from the movable fairing surface;

[0011] Step 2: The wing assembly, under the action of the torsion spring mechanism, pushes the movable fairing outward, and the wing and the movable fairing move together;

[0012] Step 3: The wing assembly detaches from the movable cover and continues to rotate;

[0013] Step 4: The wing assembly stops rotating due to the limiting action of the torsion spring fixing part, and the movable cover stops moving due to the action of the hinge;

[0014] Step 5: The fairing's aerodynamic force changes, its velocity and direction change, and it separates from the main body of the aircraft.

[0015] Compared with the prior art, the significant advantages of this invention are:

[0016] (1) The integrated fairing design avoids the problem that the two halves of the fairing are difficult to separate completely synchronously and the attitude control is difficult due to factors such as actual assembly tolerance and deviation of the force of the separation mechanism during the separation process of the split fairing.

[0017] (2) The fairing separation is completed entirely by pyrotechnics and mechanical structure, without the need for complex electronic instrument control. The structure is simple and reliable, avoiding the failure of precision instruments due to external disturbances.

[0018] (3) It has good adaptability. By unfolding the wings, the aerodynamic layout of the fairing is changed, which brings lift to the fairing. By adjusting the bearing structure to adjust the wing angle of attack and the wing shape, the efficient separation of the fast-displacement fairing under different working conditions can be achieved.

[0019] (4) The overall design has low economic cost and strong practicality. The manufacturing materials can be selected according to the needs, and the economic cost is effectively controlled while achieving the purpose of quick-disposal fairing separation.

[0020] (5) The components are mainly connected by bolts, which are easy to assemble and disassemble and have high connection strength. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of a fast-displacement fairing (wings not deployed) for a hypersonic aircraft according to the present invention.

[0022] Figure 2 This is a schematic diagram of the combination of a torsion spring, a torsion spring sleeve, and a torsion spring fixing component.

[0023] Figure 3 This is a schematic diagram of the fixed cover.

[0024] Figure 4 This is a schematic diagram of the wing assembly.

[0025] Figure 5 A schematic diagram showing the structural parameters of the wing.

[0026] Figure 6 This is a schematic diagram showing the parameter annotations for the support frame.

[0027] Figure 7 This is a schematic diagram of the overall structure of a fast-displacement fairing for a hypersonic aircraft with its wings deployed.

[0028] Figure 8 This is a schematic diagram showing the connection between the torsion spring mechanism and the fairing body.

[0029] Figure reference numerals: 1-Fairing body, 2-Modible fairing surface, 3-Hinge, 4-Explosion bolt, 5-Fixing plate, 6-Wing assembly, 7-Torsion spring assembly, 8-Boss, 9-Torsion spring, 10-Torsion spring retainer, 11-Torsion spring sleeve, 12-Fixing cover, 13-Wing, 14-Flange, 15-Bearing, 16-Cylindrical pin, 17-Flat key, 18-Gasket, 19-Support frame, Boss connecting plate 19-1, Connecting frame 19-2, Fixing component connecting plate 19 -3, H1 - Height of the top surface of the elongated window from the first section, L1 - Axial length of the movable cover surface projected onto the central axis, H2 - Maximum thickness of the wing, L2 - Length of the boss, L3 - Vertical distance from the centroid of the support frame fixing plate to the front end face of the fixing frame, L4 - Length of the support frame boss connecting plate, L5 - Half wingspan of the wing, d1 - Outer diameter of the torsion spring sleeve, d2 - Inner diameter of the torsion spring sleeve, d3 - Wire diameter of the torsion spring, d4 - Diameter of the torsion spring, R - Radius of the rear end face of the fairing. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0031] like Figures 1 to 8 As shown, this invention discloses a fast-displacement fairing for a hypersonic vehicle, comprising:

[0032] The fairing consists of a main body 1, a support frame 19, two torsion spring mechanisms 7, two wing assemblies 6, and four movable fairing surfaces 2. The rear end of the fairing main body 1 is connected to the aircraft body via explosive bolts 4. Two elongated windows are opened on the outer wall of the fairing main body 1. The four movable fairing surfaces 2 are paired together and connected to the elongated windows of the fairing main body 1 via hinges 3. Each pair of movable fairing surfaces 2 can be opened and closed by rotating outward via hinges 3. The fairing main body 1 has two bosses 8 inside. The bosses 8 and the support frame 19 are fixed to the inner wall of the fairing main body 1. The bosses 8 are close to the front end of the movable fairing surfaces 2. The bosses 8 and the support frame 19 are used to connect the fairing main body 1 and the torsion spring mechanism 7. A wing assembly 6 is provided between each pair of movable fairing surfaces 2. The torsion spring mechanism 7 is connected to the wing assembly 6 via bearings 15.

[0033] Let the horizontal section passing through the central axis of the fairing body 1 be the first section. The two elongated windows are symmetrical about the first section. The height of the top and bottom surfaces of the elongated windows from the first section is H1. Therefore, the height of the elongated windows is 2H1. R is the radius of the rear end face of the fairing body 1. When the height H1 is small, the influence of the elongated window on the start-up layout can be reduced. The axial length of the elongated window projected onto the central axis of the fairing body 1 is L1. The midpoint of the axial L1 should be between the top of the fairing body 1 and the center of gravity of the fairing body 1 to ensure the start-up layout when the wing 13 is deployed. In order to prevent the movable fairing 2 from opening freely outward, several fixed plates 5 are provided on the same group of movable fairing 2. The fixed plates 5 are connected to the inner wall of the fairing body 1 by explosion bolts 4.

[0034] The torsion spring mechanism 7 includes a torsion spring 9, a fixing cover 12, a torsion spring fixing member 10, and two torsion spring sleeves 11. The torsion spring 9 is fitted with torsion spring sleeves 11 at both ends. The assembled torsion spring sleeves 11 and torsion spring 9 are installed into the torsion spring fixing member 10. The outer wall of the torsion spring fixing member 10 has two arc-shaped limiting openings. The two torsion spring sleeves 11 extend outward from the two arc-shaped limiting openings respectively. The angle of the wing 13 can be controlled through the limiting openings, and it works in conjunction with the support frame 19 to avoid interference. The fixing cover 12 is inserted into the center of the torsion spring fixing member 10 to prevent the torsion spring 9 from moving.

[0035] The structural parameters of the torsion spring sleeve 11 are determined according to the following geometric relationships:

[0036] ,

[0037] ,

[0038] Where d1 is the outer diameter of torsion spring sleeve 11, d2 is the inner diameter of torsion spring sleeve 11, and d3 is the wire diameter of torsion spring 9.

[0039] The torsion spring fixing component 10 consists of two parts: a cylinder and a cuboid base on the cylinder. Limiting openings are opened at both ends, and the width of the limiting openings is equal to the outer diameter d1 of the torsion spring sleeve 11, thereby achieving partial fixation of the torsion spring sleeve.

[0040] The top of the fixing cover 12 is an end cover, and a positioning frustum is provided below it. The outer diameter of the frustum is the same as the inner diameter of the cylinder of the torsion spring fixing member 10. A positioning cylinder is provided below the positioning frustum, and its outer diameter is the same as the inner diameter of the torsion spring 9. The end face of the positioning cylinder is in close contact with the inner end face of the torsion spring fixing member 10 to fix the torsion spring 9.

[0041] The distance between the upper and lower surfaces of the boss 8 is L2, and the rear surface of the boss 8 coincides with the front surface of the movable cover 2. .

[0042] The support frame 19 includes a boss connecting plate 19-1, a fixing connecting plate 19-3, and two connecting frames 19-2. The two connecting frames 19-2 are fixed parallel to each other on the inner wall of the boss connecting plate 19-1, and the front ends of the two connecting frames 19-2 extend out of the boss connecting plate 19-1 and connect to the fixing connecting plate 19-3. The boss connecting plate 19-1 is connected to the boss 8, and the fixing connecting plate 19-3 is connected to the torsion spring fixing member 10. In order to make the central axis of the wing 13 and the central axis of the fairing body 1 in the same plane, the centroid of the fixing connecting plate 19-3 should satisfy the following formula:

[0043] ,

[0044] Where L3 is the vertical distance from the centroid of the fastener connecting plate 19-3 to the front end face of the boss connecting plate 19-1, L4 is the length of the boss connecting plate 19-1, and d4 is the diameter of the torsion spring 9.

[0045] The wing assembly 6 includes a wing 13, a flange 14, a pin 16, a key 17, and a gasket 18. The root of the wing 13 is connected to the flange 14, with a gasket 18 installed between them. One end of the bearing 15 is connected to the wing 13 via the key 17, and the other end of the bearing 15 is connected to the torsion spring sleeve 11 via the pin 16.

[0046] To ensure that wing 13 can deploy smoothly without interference and to provide sufficient aerodynamic force, the structural parameters of wing 13 should satisfy the following geometric relationships:

[0047] ,

[0048] ,

[0049] Where L5 is the length of wing 13 and H2 is the maximum thickness of wing 13.

[0050] There is an angle between the keyway normal of bearing 15 and the central axis of pin 16, ranging from -20° to 20°. By adjusting this angle, the angle of attack of wing 13 can be set.

[0051] In the unseparated state, the wing 13 is kept in contact with the surface of the movable cover 2 or the fixed plate 5 by the torsion spring mechanism 7 and the fixed movable cover 2. The fixing effect of the fixed plate 5 can prevent the movable cover 2 from opening freely outward while restricting the rotation of the wing 13.

[0052] The present invention discloses a method for separating a fast-displacement fairing of a hypersonic aircraft, comprising the following steps:

[0053] Step 1: Detonate the explosive bolt 4, unlock the fairing body 1 from the aircraft body, unlock the fixing plate 5, and separate it from the movable fairing surface 2;

[0054] Step 2: The wing assembly 6 is pushed outward by the torsion spring mechanism 7, and the wing 13 moves together with the movable cover 2.

[0055] Step 3: Wing assembly 7 detaches from movable cover 2 and continues to rotate;

[0056] Step 4: The wing assembly 7 stops rotating due to the limiting port of the torsion spring fixing part 10, and the movable cover 2 stops moving due to the action of the hinge 3;

[0057] Step 5: The fairing's aerodynamic force changes, its velocity and direction change, and it separates from the main body of the aircraft.

[0058] As described above, this invention has a simple structure, is easy to assemble, and has strong anti-interference capabilities. Compared with traditional separate fairing detachment methods, using this invention can reduce the complexity of the separation mechanism and improve the overall reliability of the device. Changing the wing design allows it to adapt to a wider range of scenarios, demonstrating good versatility.

Claims

1. A hypersonic aircraft rapid deployable fairing, characterized by: The system includes a fairing body (1), a support frame (19), two torsion spring mechanisms (7), two wing assemblies (6), and four movable fairing surfaces (2). The rear end of the fairing body (1) is connected to the aircraft body via explosive bolts (4), and two elongated windows are opened on the outer wall of the fairing body (1). The four movable fairing surfaces (2) are arranged in pairs and connected to the elongated windows of the fairing body (1) via hinges (3). One pair of movable fairing surfaces (2) is connected via hinges (3). Rotate outwards to open and close; the fairing body (1) is provided with two bosses (8), the bosses (8) and the support frame (19) are fixed to the inner wall of the fairing body (1), the bosses (8) are close to the front end of the movable fairing surface (2), the bosses (8) and the support frame (19) are used to connect the fairing body (1) and the torsion spring mechanism (7); a wing assembly (6) is provided between a set of movable fairing surfaces (2), and the torsion spring mechanism (7) and the wing assembly (6) are connected by a bearing (15).

2. The hypersonic aircraft fast-displacement fairing according to claim 1, characterized in that: Let the horizontal section passing through the central axis of the fairing body (1) be the first section. The two elongated windows are symmetrical about the first section. The height of the top and bottom surfaces of the elongated windows from the first section is H1. Therefore, the height of the elongated windows is 2H1. R is the radius of the rear end face of the fairing body (1); the axial length of the long strip window projected onto the central axis of the fairing body (1) is L1; the midpoint of the axial L1 should be between the top of the fairing body (1) and the center of gravity of the fairing body (1); in order to prevent the movable fairing surface (2) from opening freely outward, several fixed plates (5) are provided on the same set of movable fairing surfaces (2), and the fixed plates (5) are connected to the inner wall of the fairing body (1) by explosion bolts (4).

3. The hypersonic aircraft fast-displacement fairing according to claim 2, characterized in that: The torsion spring mechanism (7) includes a torsion spring (9), a fixing cover (12), a torsion spring fixing component (10), and two torsion spring sleeves (11). The torsion spring (9) is fitted with torsion spring sleeves (11) at both ends. The assembled torsion spring sleeves (11) and torsion spring (9) are installed into the torsion spring fixing component (10). Two arc-shaped limiting ports are opened on the outer wall of the torsion spring fixing component (10). The two torsion spring sleeves (11) extend outward from the two arc-shaped limiting ports respectively. The fixing cover (12) is inserted into the center of the torsion spring fixing component (10) to prevent the torsion spring (9) from moving.

4. The hypersonic aircraft fast-displacement fairing according to claim 3, characterized in that: The distance between the upper and lower surfaces of the boss (8) is L2, and the rear surface of the boss (8) coincides with the front surface of the movable cover (2). .

5. A fast-spinning fairing for a hypersonic aircraft according to claim 4, characterized in that: The support frame (19) includes a boss connecting plate (19-1), a fastener connecting plate (19-3), and two connecting frames (19-2); the two connecting frames (19-2) are fixed parallel to the inner wall of the boss connecting plate (19-1), and the front ends of the two connecting frames (19-2) extend out of the boss connecting plate (19-1) and are connected to the fastener connecting plate (19-3); the boss connecting plate (19-1) is connected to the boss (8), and the fastener connecting plate (19-3) is connected to the torsion spring fastener (10); the centroid of the fastener connecting plate (19-3) should satisfy the following formula: ， Where L3 is the vertical distance from the centroid of the fastener connecting plate (19-3) to the front end face of the boss connecting plate (19-1), L4 is the length of the boss connecting plate (19-1), and d4 is the diameter of the torsion spring (9).

6. A fast-displacement fairing for a hypersonic aircraft according to claim 5, characterized in that: The wing assembly (6) includes a wing (13), a flange (14), a pin (16), a key (17), and a gasket (18); the root of the wing (13) is connected to the flange (14), and a gasket (18) is installed between the two. One end of the bearing (15) is connected to the wing (13) via the key (17), and the other end of the bearing (15) is connected to the torsion spring sleeve (11) via the pin (16).

7. A fast-spinning fairing for a hypersonic aircraft according to claim 6, characterized in that: The structural parameters of the wing (13) satisfy the following geometric relationships: ， ， Where L5 is the length of the wing (13) and H2 is the maximum thickness of the wing (13).

8. A fast-displacement fairing for a hypersonic aircraft according to claim 7, characterized in that: There is an angle between the keyway normal of the bearing (15) and the central axis of the pin (16) ranging from -20° to 20°, which is the angle of attack of the wing (13).

9. A fast-displacement fairing for a hypersonic aircraft according to claim 8, characterized in that: In the unseparated state, the wing (13) is in contact with the surface of the movable cover (2) or the fixed plate (5) by the action of the torsion spring mechanism (7) and the fixed movable cover (2).

10. An aerodynamic separation method based on the fast-slinging fairing of a hypersonic vehicle according to any one of claims 1 to 9, characterized in that, Includes the following steps: Step 1: Detonate the explosive bolt (4), unlock the fairing body (1) from the aircraft body, unlock the fixed plate (5), and separate it from the movable fairing surface (2); Step 2: The wing assembly (6) is pushed outward by the torsion spring mechanism (7), and the wing (13) and the movable cover (2) move together; Step 3: The wing assembly (6) detaches from the movable cover (2) and continues to rotate; Step 4: The wing assembly (6) stops rotating due to the limiting port of the torsion spring fixing part (10), and the movable cover (2) stops moving due to the action of the hinge (3); Step 5: The fairing's aerodynamic force changes, its velocity and direction change, and it separates from the main body of the aircraft.

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