Unpowered launch vehicle folding control surface release system

Abstract

The application provides a non-electric launching aircraft folding control surface unlocking system, which activates a mechanical detonator (106) through a steel wire pull rope (5) fixed on an aircraft hanger (10) to activate a puller (2) through a detonating cord (3), the puller (2) releases the constraint on a control surface (402), and the control surface (402) is unfolded to a position and reliably locked. The non-electric launching aircraft folding control surface unlocking system realizes that the control surface can be quickly unlocked, unfolded and reliably locked after the aircraft is separated from the carrier by launching, reduces the risk of roll and uncontrollable attitude of the aircraft body, and provides protection for the success of the aircraft launching flight test.

Description

Technical Field

[0001] This invention relates to aircraft folding control surface unlocking technology, specifically, to an aircraft folding control surface unlocking system that does not require power to launch. Background Technology

[0002] Currently, aircraft control surfaces generally employ fixed integral control surfaces or foldable control surfaces. Fixed integral control surfaces occupy a larger volume, which is unfavorable for internal weapon mounting designs. Foldable control surfaces typically utilize mechanical structures combined with pyrotechnic devices or servo motor deflection to unlock the control surfaces, but this requires the aircraft to supply power to the aircraft. If a power outage or communication failure occurs during launch, the launch will be aborted, resulting in a failed flight test.

[0003] Therefore, the existing aircraft folding control surface unlocking method has stringent requirements for the power supply or communication capabilities between the carrier aircraft and the aircraft, resulting in poor aircraft adaptability and room for improvement. Summary of the Invention

[0004] To address the shortcomings of existing technologies, the purpose of this invention is to provide a non-electrically powered launch aircraft folding control surface unlocking system.

[0005] According to the present invention, a non-electrically launched aircraft folding control surface unlocking system includes: a mechanical activation component 1, a pin puller 2, a detonating cord 3, a folding control 4, and a steel wire rope 5; the mechanical activation component 1 includes a push rod 103 and a mechanical detonator 106; the mechanical detonator 106 includes a mechanical puller safety pin 10601 and a mechanical puller firing pin 10602; the pin puller 2 includes a pin puller pin shaft 201; the folding control 4 includes a control surface 402, a torsion spring 405, and a hook 406, the hook 406 being provided with a hook positioning hole 4061.

[0006] One end of the steel wire rope 5 is connected to the aircraft pylon 10, and the other end of the steel wire rope 5 is connected to the end of the mechanical puller safety pin 10601 of the mechanical activation component 1. The mechanical puller safety pin 10601 prevents the top rod 103 from being pulled apart before being pulled out by the steel wire rope 5. One end of the detonating cord 3 is connected to the mechanical activation component 1, and the other end of the detonating cord 3 is connected to the puller pin 2. The puller pin 201 of the puller pin 2 is set in the hook positioning hole 4061 of the folding rudder 4 to restrain the hook 406 of the rudder surface 402.

[0007] Preferably, during the ejection separation process of the aircraft, the safety pin 10601 of the mechanical puller of the mechanical activation component 1 is pulled out by the steel wire rope 5 fixed on the aircraft pylon 10, and the firing pin 10602 of the mechanical puller of the mechanical activation component 1 is pulled apart by the push rod 103 of the mechanical activation component 1 to activate the mechanical detonator 106.

[0008] Preferably, when the mechanical detonator 106 is activated, energy is transferred to the detonating cord 3 connected to the pin puller 2 to activate the pin puller 2. The pin puller pin 201 of the pin puller 2 retracts from the hook positioning hole 4061 of the folding rudder 4, releasing the constraint on the hook 406 of the rudder surface 402.

[0009] Preferably, the hook 406 rotates out of the cabin 7 under the action of the torsion spring 405, thereby unlocking the control surface 402 in the folded state. The control surface 402 continues to rotate under the action of the torsion spring 405, and is reliably locked after being unfolded into place.

[0010] Preferably, the folding rudder 4 is in a folded state for daily storage, transportation, and aircraft rack 10.

[0011] Preferably, the folding rudder 4 includes a connecting shaft 407; the rudder surface 402 is press-fitted with the pin 201 of the puller pin 406 through the hook positioning hole 4061 of the hook 406 of the folding rudder 4, and the rudder surface 402 is locked by restricting the rotation of the hook 406 around the connecting shaft 407.

[0012] Preferably, it includes: a lifting lug 8 and an aircraft mounting bracket 10;

[0013] The aircraft is mounted below the aircraft pylon 10 via the lug 8.

[0014] Preferably, when the aircraft is launched by catapult, the aircraft pylon 10 releases the lug 8 after receiving the aircraft launch command, and at the same time the top rod of the aircraft pylon 10 extends under the action of internal combustion gases to eject the aircraft from the aircraft.

[0015] Preferably, the lifting lug 8 includes a front first lifting lug 801 and a rear second lifting lug 802; the mechanical activation component 1 is located below the first lifting lug 801.

[0016] Preferably, the other end of the wire rope 5 is connected to the tail end of the mechanical puller safety pin 10601 of the mechanical activation component 1, and the head end of the mechanical puller safety pin 10601 is located below the tail end of the mechanical puller safety pin 10601.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] This invention enables the control surfaces to be quickly unlocked, deployed, and reliably locked after the aircraft separates from the carrier aircraft when the aircraft is not supplying power to it. This reduces the risk of the aircraft body rolling or becoming uncontrollable, and provides a guarantee for the success of the aircraft launch and flight test. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0020] Figure 1 This is a structural comparison diagram of the folded state of the non-electrically powered launch vehicle folding control surface unlocking system of the present invention from multiple perspectives.

[0021] Figure 2 This is a structural comparison diagram of the mechanical activation component 1 of the non-electrically launched aircraft folding control surface unlocking system of the present invention from multiple perspectives in the locked state.

[0022] Figure 3 This is a structural comparison diagram of the folding rudder 4 of the present invention from multiple perspectives.

[0023] Figure 4 This is a structural comparison diagram of the control surface 402 of the present invention from multiple perspectives.

[0024] Figure 5 This is a structural comparison diagram of the unlocked state structure of the non-electrically powered launch vehicle folding control surface unlocking system of the present invention from multiple perspectives.

[0025] Figure 6 This is a structural comparison diagram of the mechanical activation component 1 of the non-electrically powered launch aircraft folding control surface unlocking system of the present invention from multiple perspectives of the unlocked state.

[0026] Figure 7 This is a structural comparison diagram of the unlocked and unfolded states of the folding rudder 4 of the non-electrically powered launch vehicle folding control surface unlocking system of the present invention from multiple perspectives.

[0027] Figure 8 This is a schematic diagram of the mechanical initiator 106 of the non-electrically launched aircraft folding control surface unlocking system of the present invention.

[0028] Figure 9 This is a schematic diagram of the structure of the pin puller 2 of the non-electrically powered launch aircraft folding control surface unlocking system of the present invention.

[0029] Figure 10 This is a schematic diagram of the hook 406 of the non-electrically powered launch aircraft folding control surface unlocking system of the present invention.

[0030] Figure 11 This is a schematic diagram of the pin-pulling assembly section 6 of the non-electrically powered launch aircraft folding control surface unlocking system of the present invention.

[0031] Figure 12 This is a schematic diagram of the structure of the aircraft pylon 10 of the non-electrically powered aircraft folding control surface unlocking system of the present invention.

[0032] Figure 13 for Figure 1 A magnified view of a specific area.

[0033] Figure 14for Figure 1 A magnified view of another area.

[0034] Figure 15 for Figure 1 Another enlarged view of a local area.

[0035] Figure 16 for Figure 1 A schematic diagram of the detonation unlocking component.

[0036] The diagram shows:

[0037] Detailed Implementation

[0038] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0039] The non-powered launch vehicle folding control surface unlocking system of this invention enables the control surfaces to be quickly unlocked, deployed, and reliably locked after the aircraft is ejected from the carrier aircraft without the aircraft supplying power. This reduces the risk of the aircraft body rolling and becoming uncontrollable, and provides a guarantee for the success of the aircraft launch flight test.

[0040] like Figure 1 As shown, the non-electrically powered launch aircraft folding control surface unlocking system provided by the present invention comprises: a mechanical activation component 1, a pin puller 2, a detonating cord 3, a folding control 4, a steel wire rope 5, a pin puller mounting section 6, a cabin 7, a servo motor 9, a lifting lug 8, an aircraft pylon 10, and other auxiliary equipment.

[0041] like Figure 2 As shown, the mechanical activation component 1 includes: a base 101, a compression spring 102, a push rod 103, a limiting block 104, a positioning screw 105, a mechanical detonator 106, and a limiting screw 107, etc.; the mechanical detonator 106 includes a mechanical puller safety pin 10601 and a mechanical puller firing pin 10602.

[0042] like Figure 3 As shown, the folding rudder 4 includes: rudder base 401, rudder surface 402, torsion spring 403, torsion head 404, torsion spring 405, hook 406, connecting shaft 407, etc.

[0043] The aircraft folding rudder 4 is in a folded state during normal storage, transportation and aircraft rack 10. That is, the rudder surface 402 is in an interference fit with the pin shaft 201 of the puller pin 406 through the hook positioning hole 4061 of the folding rudder 4. By restricting the rotation of the puller pin 406 around the connecting shaft 407, the rudder surface 402 is reliably locked.

[0044] Airborne aircraft are typically securely fixed to aircraft pylons via two front and rear lugs 8 and a braking anti-sway zone on the fuselage. When the aircraft is launched by catapult, after receiving the launch command, the aircraft pylon 10 releases the lugs 8, and at the same time, the top rod of the aircraft pylon 10 extends rapidly under the action of internal combustion gases to eject the aircraft from the aircraft.

[0045] During the ejection separation process of the aircraft, the safety pin 10601 of the mechanical ejector is pulled out by the steel wire rope 5 fixed on the aircraft pylon 10. At this time, the firing pin 10602 of the mechanical ejector is pulled apart by the push rod 103 of the mechanical activation component 1, thereby activating the mechanical detonator 106. After the mechanical detonator 106 is activated, the detonating cord 3 connected to the ejector pin 2 transmits energy to the ejector pin 2 and activates the ejector pin. The ejector pin 201 quickly retracts from the hook positioning hole 4061 of the folding rudder 4, thereby releasing the constraint on the hook 406 of the rudder surface 402. At this time, the hook 406 quickly rotates out of the cabin 7 under the action of the torsion spring 405, thereby unlocking the rudder surface 402 in the folded state. The rudder surface 402 continues to rotate under the action of the torsion spring, and after unfolding into place, it is reliably locked.

[0046] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0047] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, 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. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A folding control surface unlocking system for a non-powered launch vehicle, characterized in that, include: The mechanical activation component (1), the pin puller (2), the detonating cord (3), the folding rudder (4), and the steel wire rope (5) are included. The mechanical activation component (1) includes a top rod (103) and a mechanical detonator (106). The mechanical detonator (106) includes a mechanical puller safety pin (10601) and a mechanical puller firing pin (10602). The pin puller (2) includes a pin puller pin shaft (201). The folding rudder (4) includes a rudder surface (402), a torsion spring (405), and a hook (406). The hook (406) is provided with a hook positioning hole (4061). One end of the wire rope (5) is connected to the aircraft rack (10), and the other end of the wire rope (5) is connected to the end of the mechanical puller safety pin (10601) of the mechanical activation component (1). The mechanical puller safety pin (10601) prevents the top rod (103) from being pulled apart before being pulled out by the wire rope (5). One end of the detonating cord (3) is connected to the mechanical activation component (1), and the other end of the detonating cord (3) is connected to the puller (2). The puller pin (201) of the puller (2) is set in the hook positioning hole (4061) of the folding rudder (4) to constrain the hook (406) of the rudder surface (402).

2. The folding control surface unlocking system for a non-powered launch vehicle according to claim 1, characterized in that, During the ejection separation process of the aircraft, the safety pin (10601) of the mechanical puller of the mechanical activation component (1) is pulled out by the steel wire rope (5) fixed on the aircraft pylon (10). The mechanical puller striker (10602) of the mechanical activation component (1) is pulled apart and activated by the push rod (103) of the mechanical activation component (1).

3. The folding control surface unlocking system for a non-powered launch vehicle according to claim 2, characterized in that, When the mechanical detonator (106) is activated, energy is transferred to the detonating cord (3) connected to the pin puller (2) and the pin puller (2) is activated. The pin puller pin (201) of the pin puller (2) retracts from the hook positioning hole (4061) of the folding rudder (4) and releases the constraint on the hook (406) of the rudder surface (402).

4. The folding control surface unlocking system for a non-powered launch vehicle according to claim 3, characterized in that, The hook (406) rotates out of the cabin (7) under the action of the torsion spring (405), so as to unlock the rudder surface (402) in the folded state. The rudder surface (402) continues to rotate under the action of the torsion spring (405), and is reliably locked after unfolding into place.

5. The folding control surface unlocking system for a non-powered launch vehicle according to claim 1, characterized in that, The folding rudder (4) is in a folded state during daily storage and transportation.

6. The folding control surface unlocking system for a non-powered launch vehicle according to claim 5, characterized in that, The folding rudder (4) includes a connecting shaft (407); the hook positioning hole (4061) of the hook (406) of the folding rudder (4) is interference-fitted with the pin shaft (201) of the puller, and the rudder surface (402) is locked by restricting the hook (406) from rotating around the connecting shaft (407).

7. The folding control surface unlocking system for a non-powered launch vehicle according to claim 1, characterized in that, include: Lifting lugs (8), aircraft mounting brackets (10); The aircraft is mounted below the aircraft pylon (10) via a lug (8).

8. The folding control surface unlocking system for a non-powered launch vehicle according to claim 7, characterized in that, When the aircraft is launched by catapult, the aircraft pylon (10) releases the lug (8) after receiving the launch command from the aircraft. At the same time, the top rod of the aircraft pylon (10) extends under the action of internal gas to eject the aircraft from the aircraft.

9. The folding control surface unlocking system for a non-powered launch vehicle according to claim 7, characterized in that, The lug (8) includes a first lug (801) at the front and a second lug (802) at the rear; the mechanical activation component (1) is located below the first lug (801).

10. The folding control surface unlocking system for a non-powered launch vehicle according to claim 1, characterized in that, The other end of the wire rope (5) is connected to the tail end of the mechanical puller safety pin (10601) of the mechanical activation component (1), and the head end of the mechanical puller safety pin (10601) is located below the tail end of the mechanical puller safety pin (10601).

Images