Aircraft pushing and punching device

Abstract

The invention provides an aircraft pushing and punching device. The aircraft pushing and punching device comprises a cylinder assembly, at least one actuator cylinder, at least one fire pushing and punching device and a tray. A lifting rod and a piston are arranged in the actuating cylinder, one end of the lifting rod penetrates out of the actuating cylinder and extends to be fixedly connected with the tray, the other end of the lifting rod is fixedly connected with the piston, the outer ring face of the piston is attached to the inner side face of the actuating cylinder and can slide in the axial direction of the actuating cylinder, and the hot work pushing and punching device is fixed in an end cover at the end, penetrating out of the lifting rod, of the actuating cylinder. The tail end of the aircraft is arranged on the tray; a central long blind hole is formed in the lifting rod, the central long blind hole penetrates through the lifting rod and is communicated with an inner cavity of the actuating cylinder, and a drainage hole communicated with the central long blind hole is formed in the lifting rod; the hot work pushing and punching device works to generate gas, the gas enters the rod cavity and pushes the piston to move in the first direction, the piston drives the lifting rod to move in the first direction, and when the drainage hole in the lifting rod is communicated with the rod cavity, the gas in the rod cavity enters the rodless cavity through the central long blind hole.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft launch, and specifically, to an aircraft thrust impulse device. Background Art

[0002] As a core component of the aircraft launch system, during the cold launch of an aircraft, the thrust impulse device needs to eject the aircraft from the launch device according to the system instructions and ensure that the aircraft reaches the specified ejection speed and a stable flight attitude.

[0003] The existing patent document with the publication number CN116447922A discloses a flexible tail thrust system for a launch tube and a launch tube, including: a tube body, a missile 1, a flexible tail seat 10, and a gas generator 5; the missile 1 is located inside the tube body; the missile 1 is located in front of the flexible tail seat 10, and the tail of the missile 1 is axially constrained by the flexible tail seat 10; the gas generator 5 is located in the initial cavity at the rear side of the flexible tail seat 10.

[0004] The existing patent document with the publication number CN109159908A discloses a single-lifting double-guide rail ejection mechanism, including an ejection frame, and a main guide rail, a secondary guide rail, a piston cylinder, a gas piston, a buffer, a lifting rod, and a support plate arranged on the ejection tube; the aircraft is slidably connected to the main guide rail through an aircraft lower slider and an aircraft upper slider; the main guide rail and the secondary guide rail are symmetrically installed on both sides of the lifting rod and are parallel to each other; the piston cylinder is fixedly connected to the ejection tube, and the gas piston can move up and down inside it; the buffer is fixedly connected to the lower part of the piston cylinder, and during the aircraft ejection process, it has a strong impact with the support plate to play a buffering role; the lifting rod passes through the buffer, and the upper part is fixedly connected to the gas piston, and the lower part is fixedly connected to the support plate.

[0005] Currently, the commonly used methods are mostly tail-thrust and single-side lifting launch methods, and these two ejection methods have the following problems:

[0006] 1) The tail-thrust method requires a large axial space, and additional rail constraints are needed for ejection. Otherwise, after the projectile exits the tube, the attitude of the aircraft exiting the tube is unstable.

[0007] 2) When a large-load aircraft uses single-side lifting launch, it will generate a large eccentric moment on the thrust impulse device. To balance the eccentric moment, main and secondary guide rails need to be arranged, making the cross-section of the ejection mechanism, which is originally circular, become rectangular, resulting in poor overall rigidity.

[0008] 3) During the single-side lifting launch process of a large-load aircraft, due to the launch vibration, the aircraft slider will generate a rolling moment on the aircraft, and the attitude of the aircraft exiting the tube is poor.

[0009] 4) For the two lifting methods, after the ejection ends, the gas flow will leak out from the actuator, which will pose a hazard to the equipment inside the launch tube. Moreover, the braking method is single, and the braking stack has a poor ability to absorb energy during high-speed braking.

[0010] The above-mentioned lifting methods cannot be applied when the axial space of the launch device is insufficient and the requirements for the ejection attitude and force of the aircraft are relatively high, which brings risks to the launch. Therefore, it is of great significance to develop a new type of cold ejection mechanism for aircraft. Summary of the Invention

[0011] Aiming at the defects in the prior art, the purpose of the present invention is to provide a push-punch device for an aircraft.

[0012] According to a push-punch device for an aircraft provided by the present invention, it includes a cylinder body assembly, at least one actuator, at least one pyrotechnic push-puncher, and a tray;

[0013] The actuator, the aircraft, and the tray are all arranged inside the cylinder body assembly. A lifting rod and a piston are arranged inside the actuator. One end of the lifting rod passes through the actuator and extends to be fixedly connected to the tray. The other end of the lifting rod is fixedly connected to the piston. The outer ring surface of the piston fits against the inner side surface of the actuator and can slide along the axial direction of the actuator. The pyrotechnic push-puncher is fixed inside the end cover at one end of the actuator where the lifting rod passes through. The tail end of the aircraft is arranged on the tray;

[0014] A central long blind hole is arranged inside the lifting rod. The central long blind hole penetrates through the lifting rod and communicates with the inner cavity of the actuator. A drainage hole communicating with the central long blind hole is arranged on the lifting rod;

[0015] The gas generated by the operation of the pyrotechnic push-puncher enters the rod chamber and pushes the piston to move in the first direction. The piston drives the lifting rod to move in the first direction. When the drainage hole on the lifting rod communicates with the rod chamber, the gas in the rod chamber enters the rodless chamber through the central long blind hole.

[0016] Preferably, the drainage hole extends from the outer side wall of the lifting rod to communicate with the central long blind hole, and the drainage holes are symmetrically staggered along the axial direction of the lifting rod.

[0017] Preferably, the included angle between the drainage hole and the axis of the lifting rod is 35 degrees to 55 degrees.

[0018] Preferably, the cylinder body assembly includes a cylinder body. The cylinder body is arranged on the buffer bracket through a T-shaped guiding slider. A T-shaped guiding groove is arranged on the buffer bracket. The T-shaped guiding slider is in sliding fit with the T-shaped guiding groove;

[0019] There are two T-shaped guiding sliders. The two T-shaped guiding sliders are fixed on the outer side wall of the cylinder body along the axial direction of the cylinder body.

[0020] Preferably, a brake pipe is fixed outside the end cover at one end of the actuating cylinder passing through the lifting rod, and the brake pipe is in sliding fit with the lifting rod;

[0021] The brake pipe includes an arc-shaped brake pipe, which is formed by connecting in the order of a convex arc ring, a concave arc ring, and a convex arc ring.

[0022] Preferably, it further includes an arc-shaped guide rail and an arc-shaped slider, and the aircraft slides on the arc-shaped guide rail through the arc-shaped slider;

[0023] The arc-shaped guide rail and the arc-shaped slider are both symmetrically distributed about the central axis of the aircraft;

[0024] The arc-shaped guide rail includes an arc-shaped guide rail groove, and the arc-shaped guide rail groove includes a first upper arc working surface and a first lower arc working surface, and the first upper arc working surface and the first lower arc surface share the first center of the circle;

[0025] The arc-shaped slider includes a second upper arc working surface and a second lower arc working surface, and the second upper arc working surface and the second lower arc working surface share the second center of the circle;

[0026] The first center of the circle and the second center of the circle both coincide with the center of the circle of the outer arc surface of the head of the aircraft.

[0027] Preferably, one end of the lifting rod connecting the tray includes a shoulder, and the diameter of the shoulder is greater than the diameter of the lifting rod.

[0028] Preferably, both the actuating cylinder and the pyrotechnic thruster include two, and the two actuating cylinders are symmetrically arranged on both sides of the aircraft, and both ends of the tray are respectively fixedly connected to the two lifting rods;

[0029] The tray is symmetrically arranged along the central axis of the aircraft.

[0030] Preferably, the tray includes a lifting circular plate and an L-shaped lifting plate, two pairs of L-shaped lifting plates are symmetrically connected to both sides of the lifting circular plate, and the L-shaped lifting plate is fixedly connected to the lifting rod;

[0031] Lightening holes are provided on the lifting circular plate;

[0032] The lifting circular plate is attached to the tail end of the aircraft.

[0033] Preferably, it further includes a rear cover, and the rear cover is fixedly connected to the cylinder body assembly;

[0034] The rear cover includes a cylindrical platform and a conical platform, both the cylindrical platform and the conical platform are symmetrically arranged about the central axis of the aircraft, and the cylindrical platform is arranged on the conical platform;

[0035] The cylindrical platform supports the lifting circular plate.

[0036] Compared with the prior art, the present invention has the following beneficial effects:

[0037] 1. In the present invention, a central long blind hole communicating with the inner cavity of the actuating cylinder is provided on the lifting rod, and an inclined drainage hole is provided on the lifting rod. The drainage hole communicates with the central long blind hole. When the drainage hole of the lifting rod completely passes through the pyrotechnic thruster, the gas flow in the rod chamber of the actuating cylinder is sufficiently ejected into the rodless chamber of the actuating cylinder along a certain direction through the central long blind hole to establish a reverse pressure, which is beneficial to buffering the pushing device and reducing the bounce height of the pushing device;

[0038] 2. In the present invention, a buffer bracket is provided, and a T-shaped guiding groove is provided on the buffer bracket. A T-shaped guiding slider is axially fixed outside the cylinder assembly, and the T-shaped guiding slider is slidably matched with the T-shaped guiding groove. After the aircraft separates from the cylinder assembly, the cylinder assembly slides along the T-shaped guiding groove, which is beneficial to buffering the cylinder assembly and improving the safety of aircraft launch;

[0039] 3. In the present invention, the aircraft slides on the arc-shaped guide rail through the arc-shaped slider, and the second upper arc working surface of the arc-shaped slider fits with the first upper arc working surface of the arc-shaped guide rail or the second lower arc working surface of the arc-shaped slider fits with the first lower arc working surface of the arc-shaped guide. Since these arc surfaces are concentric arc surfaces with the head arc surface of the aircraft, the vibration force received by the aircraft approximately points to the center of the circle, making the rolling moment of the aircraft around the center of the circle very small and the rolling acceleration very small;

[0040] 4. In the present invention, a shoulder is provided at the tail end of the lifting rod, and an arc-shaped brake pipe is provided at the outer end of the actuating cylinder. The diameter of the shoulder is larger than the diameter of the lifting rod, and the shoulder starts to contact the arc-shaped brake pipe to jointly brake the tray, which is beneficial to the separation of the end face of the aircraft tail from the tray;

[0041] 5. In the present invention, two actuating cylinders are symmetrically arranged on both sides of the aircraft, and equal amounts of gas are released on both sides of the aircraft. When the aircraft is launched, the pushing device will not generate a large eccentric moment, which is beneficial to the stability of the aircraft's posture when leaving the cylinder. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] By reading the following detailed description of the non-limiting embodiments with reference to the accompanying drawings, other features, objects and advantages of the present invention will become more apparent:

[0043] Figure 1 The front view of the aircraft in the aircraft pushing device before launch mainly showing the present invention;

[0044] Figure 2 Mainly showing the present invention Figure 1 View B;

[0045] Figure 3 Mainly showing the present invention Figure 1C-C view;

[0046] Figure 4 Front view mainly showing the aircraft thrust boosting device after the aircraft of the present invention is launched;

[0047] Figure 5 Mainly showing the present invention Figure 4 Partial enlarged view I;

[0048] Figure 6 Mainly showing the present invention Figure 4 D-D view;

[0049] Figure 7 Mainly showing the present invention Figure 6 Partial enlarged view II;

[0050] Figure 8 Top view of the aircraft of the present invention in the reverse course;

[0051] Figure 9 Top view mainly showing the buffer bracket of the present invention;

[0052] Figure 10 Front view mainly showing the arc-shaped brake pipe of the present invention.

[0053] Shown in the figure:

[0054] Cylinder assembly 10, support pin 23, second central hole 43

[0055] Actuating cylinder 20, lifting hole 23a, convex arc ring 51

[0056] Arc guide rail 30, piston 24, concave arc ring 52

[0057] Pyrotechnic thruster 40, lower cover 25, lifting pin 62

[0058] Arc-shaped brake pipe 50, lifting rod 26, L-shaped lifting plate 63

[0059] Tray 60, central long blind hole 27, second lifting hole 64

[0060] Rear cover 80, drainage hole 28, lifting round plate 65

[0061] Aircraft 100, shoulder 28a, relief hole 66

[0062] Arc-shaped slider 101, first lifting hole 28b, buffer bracket 70

[0063] Outer arc surface of the head 104, first central hole 29, mounting hole 71

[0064] Guide rail seat 11, through-wall hole 29a, T-shaped guide groove 72

[0065] Upper support 12, mounting seat 31, cylindrical table 81

[0066] Lower support 13, arc-shaped guide groove 32, conical table 82

[0067] Upper arc-shaped rubber pad 14, first upper arc working surface 33, foundation 90

[0068] Lower arc-shaped rubber pad 15, first lower arc working surface 34, second upper arc working surface 102, T-shaped guide slider 16, first outer retaining surface 35, second lower arc working surface 103, cylinder 17, first center 36, second outer retaining surface 105

[0069] Upper cylinder 21, nozzle 41, second center 106

[0070] Air release screw plug 22, ignition cable 42 Specific implementation mode

[0071] The present invention will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0072] As Figures 1 to 3 shown, a flight vehicle thrust impulse device provided according to the present invention includes a cylinder assembly 10, at least one actuator 20, at least one pyrotechnic thruster 40, and a tray 60; the actuator 20, the flight vehicle 100, and the tray 60 are all arranged in the cylinder assembly 10. A lifting rod 26 and a piston 24 are arranged in the actuator 20. One end of the lifting rod 26 passes through the actuator 20 and extends to be fixedly connected with the tray 60. The other end of the lifting rod 26 is fixedly connected with the piston 24. The outer ring surface of the piston 24 fits against the inner side surface of the actuator 20 and can slide along the axial direction of the actuator 20. The pyrotechnic thruster 40 is fixed in the end cover at one end of the actuator 20 where the lifting rod 26 passes through. The tail end of the flight vehicle 100 is arranged on the tray 60; a central long blind hole 27 is arranged inside the lifting rod 26. The central long blind hole 27 penetrates through the lifting rod 26 and communicates with the inner cavity of the actuator 20. A drainage hole 28 communicating with the central long blind hole 27 is arranged on the lifting rod 26. The gas generated by the work of the pyrotechnic thruster 40 enters the rod chamber and pushes the piston 24 to move in the first direction. The piston 24 drives the lifting rod 26 to move in the first direction. When the drainage hole 28 on the lifting rod 26 communicates with the rod chamber, the gas in the rod chamber enters the rodless chamber through the central long blind hole 27.

[0073] In an embodiment where the aircraft 100 needs to be launched upward, the piston 24 moves in the first direction, that is, the piston 24 moves upward along the axis of the actuating cylinder 20, and the piston 24 drives the lifting rod 26 to move upward along the axis of the actuating cylinder 20. The piston 24 is inside the actuating cylinder 20, dividing the inner cavity of the actuating cylinder 20 into two parts. The inner cavity of the actuating cylinder 20 with the lifting rod 26 is the rod chamber, and the inner cavity of the actuating cylinder 20 without the lifting rod is the rodless chamber.

[0074] A brake pipe is fixed outside the end cover at one end of the actuating cylinder 20 passing through the lifting rod 26, and the brake pipe is slidably engaged with the lifting rod 26. The brake pipe includes an arc-shaped brake pipe 50, and the arc-shaped brake pipe 50 is connected in the order of a convex arc ring 51, a concave arc ring 52, and a convex arc ring 51.

[0075] It further includes an arc-shaped guide rail 30 and an arc-shaped slider 101, and the aircraft 100 slides on the arc-shaped guide rail 30 through the arc-shaped slider 101; both the arc-shaped guide rail 30 and the arc-shaped slider 101 are symmetrically distributed about the axis of the aircraft 100; the arc-shaped guide rail 30 includes an arc-shaped guide rail groove 32, and the arc-shaped guide rail groove 32 includes a first upper arc working surface 33 and a first lower arc working surface 34, and the first upper arc working surface 33 and the first lower arc working surface 34 share a first center 36; the arc-shaped slider 101 includes a second upper arc working surface 101 and a second lower arc working surface 103, and the second upper arc working surface 101 and the second lower arc working surface 103 share a second center 106; both the first center 36 and the second center 106 are concentric with the outer arc surface of the head of the aircraft 100.

[0076] It further includes a rear cover 80, and the rear cover 80 is fixedly connected to the cylinder body assembly 10; the rear cover 80 includes a cylindrical platform 801 and a conical platform 802, and both the cylindrical platform 801 and the conical platform 802 are symmetrically arranged about the axis of the aircraft 100, and the cylindrical platform 801 is arranged on the conical platform 802.

[0077] Specifically, the aircraft thrusting device of the present invention includes a cylinder body assembly 10, an actuating cylinder 20, an arc-shaped guide rail 30, a pyrotechnic thruster 40, an arc-shaped brake pipe 50, a tray 60, a rear cover 80, and the arc-shaped slider 101 of the aircraft 100. There are two actuating cylinders 20 and two pyrotechnic thrusters 40, and the two actuating cylinders 20 are symmetrically arranged on both sides of the aircraft 100, and both ends of the tray 60 are fixedly connected to the two lifting rods 26. The actuating cylinder 20, the arc-shaped guide rail 30, the pyrotechnic thruster 40, the arc-shaped brake pipe 50, the tray 60, and the rear cover 80 are all symmetrically arranged about the axis of the aircraft.

[0078] As Figures 1 to 3As shown, the cylinder assembly 10 includes a guide rail base 11, an upper bracket 12, a lower bracket 13, an upper arc-shaped rubber pad 14, a lower arc-shaped rubber pad 15, and a cylinder 17. The cylinder 17 is preferably a circular cylinder. Four upper brackets 12 are symmetrically arranged along the center line of the cylinder 17 at the upper part of the cylinder 17. The inner ends thereof are vulcanized with upper arc-shaped rubber pads 14, and the outer ends are fastened to the cylinder 17. Four lower brackets 13 are symmetrically arranged along the center line of the cylinder 17 at the lower part of the cylinder 17. The inner ends thereof are vulcanized with lower arc-shaped rubber pads 15, and the outer ends are fastened to the cylinder 17.

[0079] After the aircraft 100 is launched, in order to buffer the cylinder assembly 10, the present invention further provides a buffer bracket 70. The buffer bracket 70 includes a mounting hole 71 and a T-shaped guide groove 72. The buffer bracket 70 is fixed to the foundation 90 through the mounting hole 71. The cylinder 17 is arranged on the buffer bracket 70 through a T-shaped guide slider 16. The T-shaped guide groove 72 provided on the buffer bracket 70 is in free sliding fit with the T-shaped guide slider 16. There are two T-shaped guide sliders 16. The two T-shaped guide sliders 16 are axially fixed on the outer side wall of the cylinder 17 along the cylinder 17. The two T-shaped guide sliders 16 are axially fixed to the cylinder 17, and the distance between them matches the free bounce height when the cylinder assembly 10 is launched.

[0080] As Figure 1 , Figure 2 , Figure 4 , Figure 5 and Figure 6 shown, the actuator cylinder 20 includes an upper cylinder body 21, a gas release screw plug 22, a support pin 23, a piston 24, a lower cover 25, and a lifting rod 26. The piston 24 is threadedly connected to the lifting rod 26. The outer ring surface of the piston 24 can smoothly slide axially within the cylinder body 21. The lower cover 25 is threadedly connected to the upper cylinder body 21 as a whole. A first central hole 29 and a through wall hole 29a are opened on the lower cover 25. A suspension hole 23a for the support pin 23 is opened at the top end of the upper cylinder body 21. The support pin 23 passes through the suspension hole 23a and the mounting hole of the upper bracket 12 to suspend the actuator cylinder 20 within the cylinder assembly 10. The outer cylindrical surface of the upper cylinder body 21 is in close contact with the upper arc-shaped rubber pad 14 and the lower arc-shaped rubber pad 15. A gas release screw plug 22 is arranged at the upper part of the upper cylinder body 21. A central long blind hole 27 communicating with the rodless cavity is opened on the lifting rod 26. A plurality of inclined drainage holes 28 are opened at the bottom of the lifting rod 26. The drainage holes 28 extend from the outer side wall of the lifting rod 26 to communicate with the central long blind hole 27. The inner ends of the drainage holes 28 are in penetration with the central long blind hole 27. The drainage holes 28 are symmetrically staggered along the axial direction of the lifting rod 26. The angle between the drainage holes 28 and the axis of the lifting rod 26 includes 35 degrees to 55 degrees, preferably 45 degrees. The tail of the lifting rod 26 includes a shoulder 28a. The width of the shoulder 28a in the direction perpendicular to the axial direction of the lifting rod 26 is greater than the width of the lifting rod 26. A first lifting hole 28b is opened on the shoulder 28a. After the actuator cylinder 20 is assembled, the air in the rodless cavity is released through the gas release screw plug 22.

[0081] As Figure 1 , Figure 2 , Figure 4 , Figure 6 and Figure 7 shown, the arc-shaped guide rail 30 includes a mounting seat 31 and an arc-shaped guide rail groove 32. The arc-shaped guide rail groove 32 includes a first upper arc working surface 33, a first lower arc working surface 34 and a first outer retaining surface 35. The first upper arc working surface 33 and the first lower arc surface 34 are concentric arc surfaces, and the concentric center is the first center 36. The first upper arc working surface 33 is connected to the first lower arc working surface 34 through the first outer retaining surface 35. The arc-shaped guide rail 30 is symmetrically arranged along its center line.

[0082] As Figure 8 shown, the aircraft 100 slides on the arc-shaped guide rail 30 through an arc-shaped slider 101. The arc-shaped slider 101 includes a second upper arc working surface 102, a second lower arc working surface 103 and a second outer retaining surface 105. Both the second upper arc working surface 102 and the second lower arc working surface 103 are concentric arc surfaces with the outer arc surface 104 of the head of the aircraft, and the concentric center is the second center 106. The second upper arc working surface 102 is connected to the second lower arc working surface 103 through the second outer retaining surface 105. The arc-shaped slider 101 is symmetrically arranged along its center line.

[0083] As Figure 7 and Figure 8 shown, R1 is the radius of the first upper arc working surface 33, R2 is the radius of the first lower arc working surface 34, R1 > R2, R3 is the radius of the second upper arc working surface 102, R4 is the radius of the second lower arc working surface 104, R3 > R4, the first center 34 coincides with the second center 106, and the first outer retaining surface 35 and the second outer retaining surface 105 are used for axially positioning the arc-shaped slider 101.

[0084] As Figure 1 , Figure 4 and Figure 6 shown, the tray 60 includes a lifting pin 62, an L-shaped lifting plate 63, a lifting circular plate 65 and a lightening hole 66. Two pairs of L-shaped lifting plates 63 are symmetrically connected to both sides of the lifting circular plate 65. A second lifting hole 64 is formed on the L-shaped lifting plate 63. The lifting pin 62 passes through the second lifting hole 64 formed on the L-shaped lifting plate 63 and the first lifting hole 28b formed on the shoulder 28a, so that the lifting rod 26 is connected to the tray 60. A plurality of lightening holes 66 for reducing its weight are uniformly arranged on the lifting circular plate 65. The tray 60 is symmetrically arranged along its center line. The aircraft 100 is loaded into the cylinder assembly 10 through the arc-shaped slider 101 and fits with the lifting circular plate 65.

[0085] As Figure 4As shown, the rear cover 80 includes a cylindrical table 81 and a conical table 82. The cylindrical table 81 is arranged at the upper part of the rear cover 80, and the conical table 82 is arranged at the lower part of the rear cover 80. The rear cover 80 is threadedly connected to the cylinder assembly 10, and the cylindrical table 81 supports and lifts the circular plate 65.

[0086] As Figure 1 and Figure 9 shown, the buffer bracket 70 includes a mounting hole 71 and a T-shaped guide groove 72. The buffer bracket 70 is fixed to the foundation 90 through the mounting hole 71. The T-shaped guide slider 16 is freely slidably fitted along the T-shaped guide groove 72. The cylinder assembly 10 is loaded into the buffer bracket 70 through the sliding fit of the T-shaped guide slider 16 along the T-shaped guide groove 72, and the conical table 82 contacts the buffer bracket 70.

[0087] As Figure 1 、 Figure 3 shown, the pyrotechnic thruster 40 includes a nozzle 41 and an ignition cable 42. The pyrotechnic thruster 40 is screwed to the upper end face of the lower cover 25, and the second central hole 43 of the pyrotechnic thruster 40 is concentric with the first central hole 29 of the lower cover 25. The ignition cable 42 is led out of the cylinder assembly 10 through the through-wall hole 29a of the lower cover 25 (not shown in the figure).

[0088] As Figure 1 and Figure 10 shown, the arc brake tube 50 is made of high-toughness stainless steel by metal cutting. It includes a convex arc ring 51 and a concave arc ring 52. The diameters of both the convex arc ring 51 and the concave arc ring 52 are R. The inner diameter of the arc brake tube 50 is D, and the outer diameter is D + 2R. The arc brake tube 50 is fixed to the lower end face of the lower cover 25 through a mounting circular plate. The first central hole 29 of the lower cover 25 is located on the straight line where the central axis of the arc brake tube 50 is located. The arc brake tube 50 is connected in the order of the convex arc ring 51, the concave arc ring 52, and the convex arc ring 51, and is slidably fitted with the lifting rod 26.

[0089] As Figure 1 and Figure 4As shown, arrow 1 indicates the heading. When the aircraft 100 is launched, according to the system launch command, two groups of ignition cables 42 ignite simultaneously. The pyrotechnic thruster 40 ejects high-pressure gas rapidly through the nozzle 41. The gas fills the rod-sealed cavity of the actuator 20. As the gas pressure continuously increases, the piston 24 moves upward simultaneously with the pull rod 26 connected to itself. Under the action of the pull rod 26, the tray 60 moves upward, thereby driving the aircraft 100 to slide upward within the arc-shaped guide rail 30. During the sliding process, due to the second upper arc working surface 102 of the arc-shaped slider 101 of the aircraft 100 fitting with the first upper arc working surface 33 of the arc-shaped guide rail 30 or the second lower arc working surface 103 of the arc-shaped slider 101 fitting with the first lower arc working surface 34 of the arc-shaped guide rail 30, and since these arc surfaces and the outer arc surface 104 of the aircraft's head are concentric circular arc surfaces, the vibration force approximately points to the center of the circle, making the rolling moment of the aircraft 100 around the center of the circle very small and the rolling acceleration very small. After the aircraft 100 slides a certain distance within the arc-shaped guide rail 30, when the drainage hole 28 of the pull rod 26 completely passes through the pyrotechnic thruster 40, the gas flow in the rod cavity is sufficiently ejected along the direction shown by arrow 2 through the central long blind hole 27 into the rodless cavity to establish a reverse pressure. At this time, the shoulder 28a starts to contact the arc-shaped brake tube 50 to implement combined braking on the tray 60, and the end face of the tail of the aircraft 100 separates from the tray 60. Finally, the aircraft 100 flies out of the thruster device by inertia.

[0090] The aircraft thruster device involved in the present invention can achieve high-speed cold launch of the aircraft 100, avoiding the problems of large eccentric torque during the launch process of traditional cold ejection devices, large rolling angular velocity of the aircraft out of the barrel, and high bounce of the thruster device after buffering, improving the launch safety and attitude stability of the aircraft. The present invention has been verified in multiple launch tests, and it is confirmed that the device meets the usage requirements.

[0091] The present invention provides an aircraft cold ejection device, which can effectively avoid the problems of eccentric torque during the aircraft launch process, gas leakage from the actuator after ejection, poor braking effect, and poor attitude of the aircraft out of the barrel, realizing rapid and safe launch of the aircraft and reducing the axial usage space.

[0092] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0093] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. An aircraft thrust device, characterized in that: It comprises a cylinder assembly (10), at least one actuator (20), at least one pyrotechnic thruster (40) and a tray (60); The actuating cylinder (20), the aircraft (100) and the tray (60) are all arranged in the cylinder assembly (10). The actuating cylinder (20) is provided with a lifting rod (26) and a piston (24). One end of the lifting rod (26) passes through the actuating cylinder (20) and extends to be fixedly connected to the tray (60). The other end of the lifting rod (26) is fixedly connected to the piston (24). The outer ring surface of the piston (24) is in contact with the inner side surface of the actuating cylinder (20) and can slide axially along the actuating cylinder (20). The pyrotechnic thruster (40) is fixed in the end cover of the end of the actuating cylinder (20) passing through the lifting rod (26). The tail end of the aircraft (100) is arranged on the tray (60). The lifting rod (26) is provided with a central long blind hole (27) inside, the central long blind hole (27) passes through the lifting rod (26) and is connected to the inner cavity of the actuator (20), and the lifting rod (26) is provided with a drainage hole (28) connected to the central long blind hole (27); The gas generated by the pyrotechnic thruster (40) enters the rod chamber and pushes the piston (24) to move along the first direction. The piston (24) drives the lifting rod (26) to move along the first direction. When the drainage hole (28) on the lifting rod (26) is connected to the rod chamber, the gas in the rod chamber enters the rodless chamber through the central long blind hole (27).

2. The aircraft thrust device according to claim 1, characterized in that: The drainage holes (28) extend from the outer wall of the lifting rod (26) to communicate with the central long blind hole (27), and the drainage holes (28) are symmetrically staggered along the axial direction of the lifting rod (26).

3. The aircraft thrust device according to claim 2, characterized in that: The included angle between the drainage hole (28) and the axis of the lifting rod (26) is in the range of 35 degrees to 55 degrees.

4. The aircraft thrust device according to claim 1, characterized in that: The barrel assembly (10) comprises a barrel (17), the barrel (17) being arranged on a buffer bracket (70) via a T-shaped guide slider (16), the buffer bracket (70) being provided with a T-shaped guide groove (72), the T-shaped guide slider (16) being slidably matched with the T-shaped guide groove (72); The T-shaped guide sliders (16) include two, and the two T-shaped guide sliders (16) are fixed to the outer side wall of the cylinder (17) along the axial direction of the cylinder (17).

5. The aircraft thrust device according to claim 1, characterized in that: A brake pipe is fixed to the outside of the end cover of one end of the actuating cylinder (20) passing through the lifting rod (26), and the brake pipe is slidably matched with the lifting rod (26); The brake pipe comprises an arc-shaped brake pipe (50), and the arc-shaped brake pipe (50) is formed by connecting a convex arc-shaped ring (51), a concave arc-shaped ring (52), and a convex arc-shaped ring (51) in sequence.

6. The aircraft thrust device according to claim 1, characterized in that: It also includes an arc-shaped guide rail (30) and an arc-shaped slider (101), and the aircraft (100) slides on the arc-shaped guide rail (30) via the arc-shaped slider (101); The arc-shaped guide rail (30) and the arc-shaped slider (101) are symmetrically distributed about the central axis of the aircraft (100); The arc-shaped guide rail (30) comprises an arc-shaped guide rail groove (32), the arc-shaped guide rail groove (32) comprises a first upper arc working surface (33) and a first lower arc working surface (34), and the first upper arc working surface (33) and the first lower arc working surface (34) share a first circle center (36); The arc-shaped sliding block (101) comprises a second upper arc working surface (102) and a second lower arc working surface (103), wherein the second upper arc working surface (102) and the second lower arc working surface (103) share a second circle center (106); The first circle center (36) and the second circle center (106) both coincide with the center of the outer arc surface (104) of the head of the aircraft (100).

7. The aircraft thrust device according to claim 1, characterized in that: One end of the lifting rod (26) connected to the tray (60) includes a shoulder (28a), and the diameter of the shoulder (28a) is larger than the diameter of the lifting rod (26).

8. The thrust device of the aircraft (100) according to claim 1, characterized in that: The actuator (20) and the pyrotechnic thruster (40) each include two actuators (20), the two actuators (20) are symmetrically arranged on both sides of the aircraft (100), and the two ends of the tray (60) are respectively fixedly connected to two lifting rods (26); The tray (60) is symmetrically arranged along the central axis of the aircraft (100).

9. The aircraft thrust device according to claim 8, characterized in that: The tray (60) comprises a lifting circular plate (65) and an L-shaped lifting plate (63), two pairs of L-shaped lifting plates (63) are symmetrically connected on both sides of the lifting circular plate (65), and the L-shaped lifting plates (63) are fixedly connected to the lifting rods (26); The lifting circular plate (65) is provided with a lightening hole (66); The lifting circular plate (65) is fitted to the tail end of the aircraft (100).

10. The aircraft thrust device according to claim 9, characterized in that: It also includes a rear cover (80), wherein the rear cover (80) is fixedly connected to the barrel assembly (10); The rear cover (80) comprises a cylindrical cone (81) and a truncated cone (82), wherein the cylindrical cone (81) and the truncated cone (82) are both symmetrically arranged about the central axis of the aircraft (100), and the cylindrical cone (81) is arranged on the truncated cone (82); The cylindrical platform (81) supports the lifting circular plate (65).

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