JPS60237147A - Tailless system control of jet aircraft - Google Patents

Abstract

PURPOSE:To perform tailless system control of jet aircraft by utilizing the jet exhaust nozzle flow and the relevant flow in the proximity of jet aircraft to use the jet flow both for propulsion and directional control through a guide damper, a grid, a tube, etc. CONSTITUTION:In order to control the direction of jet aircraft through a tailless structure, a single stage horizontally movable grid damper 5 in the vicinity of an exhaust nozzle 2 is used for lifting/lowering around a damper shaft 7 through a jet flow movable up and down while a double state vertically movable grid damper 6 is movable to the right and left around the damper shaft 7 to use the jet flow in the right/left direction. The jet flow 8 at the exhaust port 1 will lift/lower at the section 3 while propel to the right/left at the section 4 thus to serve as a rudder at the tail of conventional jet aircraft. Heat-resistance material such as carbon fiber, ceramic, titanium, etc. is employed especially at the hot portion in the jet stream and replaced in early time to achieve safety.

Description

[Detailed Description of the Invention] (Objective of the Invention) In order to control the direction of the tailless structure type of a jet aircraft, a structure such as a guiding damper, a lattice, a cylinder, etc. is created by utilizing the flow in the jet nozzle flow and the connected flow in the vicinity of the jet nozzle. This method uses jet flow for both propulsion and direction control.

(1) A method in which the direction is controlled by combining movable horizontal and vertical dampers, gratings, cylinders, and other structures in the first and second stages; (2) A method in which the nozzle direction is movable in the flexible jet nozzle to control the direction; The materials used, especially those installed in high-temperature parts of the jet flow, should be replaced at an early stage, considering the safety factor of heat-resistant materials (e.g., carbon fiber, ceramics, titanium, and others) within the service life of the bed. Measure safety using methods.

(Structure of the invention), Fig. 1, two-stage jet rudder (front view), Fig. 2
Top (cross-sectional view): Close to the injection port 2, a 1-stage horizontally movable lattice damper 5 is movable up and down around the damper shaft 7 and is used for raising and lowering in a jet flow, and a 2-stage vertically movable lattice damper 6ri is centered around the damper shaft 7. It is movable left and right, and uses the Z-style in the left-right direction.The 3 parts of the exhaust port 1 move up and down, and the 4 parts propel it in the left-right direction. (a method that uses both propulsion and directional control).

Figure 3, single-stage jet rudder (front view), Figure 4, same
Above (cross-sectional view), in the first stage near the injection port 2, the jet stream moves up and down with the shaft 7 of the horizontally movable damper 5, and the vertically movable damper 6
The jet flow moves horizontally from side to side on axis 7, and the jet flow moves left and right. ) and hard plate materials (ceramics, titanium, etc.) with flexible nozzle structure, jet flow control port at the flexible end,
The direction is controlled by controlling the jet flow control port with the control fitting 13 on the tightening bunt 2 and the control-related mounting structure 15 and the control interlock 14. Figure 8, same as above (cross-sectional view), Horizontal dampers 5il- are moved up and down by the shaft 7 above and below the outer circumference of the injection port 2, and vertical dampers 6 are placed on the left and right sides of the outer circumference of the injection port 2 to move up and down in a jet-linked flow. Propulsion in the direction, Figure 9, Reverse jet lining around the injection nozzle (cross-sectional view), Figure 4 of the combination of the jet reverser and single-stage rudder for the jet nozzle, and the reverse jet shell during navigation (not in use) )
18 shows the position of the reverse jet tensioner in motion (in use). The tensioner rotates around the center shaft 7, and the cent flow is used for braking by the reverse jet flow.

(Effects of the invention) The features of the tailless wing control system for jet aircraft include the following: ( 1) Significant reduction in air resistance, (2) Increase in speed, (3) Reduction in fuel consumption, (4) Advantages in aircraft structural mechanics, (5) Increase in payload weight with the same engine output, (6) Construction costs are low due to reduced manufacturing materials and quantity, shorter construction period, smaller size and lighter weight, smaller hangar, easier loading and unloading, (7) Simplified maneuverability with less transmission torque, greater safety due to being unaffected by water clouds, (8) ) Expansion of rear visibility (advantageous for military use), (9) There are many other advantages. (Note) The direction of the aircraft's traveling characteristics can be corrected by fine-tuning the basic angle of the damper and others.

[Brief explanation of the drawing]

Figure 1, two-stage jet rudder (front view), Figure 2, same
Top (cross-sectional view), A diagram of a two-piece system with an elevating lattice damper on the inside in the jet flow close to the injection port, and a left-right lattice damper on the outside; Figure 3: A single-stage rudder for the injection port (front view); Figure 4, same
Top (cross-sectional view), Figure 5: Injection nozzle flexible/pull rudder (front view), Figure 6, same as above. (Cross-sectional view), Flexible/pull material (carbon fiber, cylindrical) and hard board material combination type (petal) at the injection port, which can be freely controlled using a tightening band and metal fittings, Figure 7, Fumarole outer damper rudder (front view) ) Figure 8, same
Top (cross-sectional view), The outer circumference of the injection nozzle is raised and lowered by the vertical movement of a horizontal damper, and the outer circumference of the injection nozzle is moved left and right by the left and right vertical tappers. The reverse jet tension body is attached to the jet nozzle, and the horizontal and vertical lines enter one stage in the jet flow of the nozzle.The fourth figure shows the reverse jet string in operation (braking), (symbol name), 1-Exhaust port, 2 - Injection port, 3 - One-way rudder 1st stage part, 4 - One-way rudder 2nd stage part, 5 - Elevator (damper), 6 - Left and right rudder (
damper), 7-axis, 8-jet discharge flow direction, 9-reinforcement material, 10-flexible material, 11-jet flow control port,)
2-tightening band, 13-control fitting, 14-control interlock, 1
5-Control-related mounting inner cylinder frame structure, 16-Mounting frame structure, 17
- Reverse jet shell during navigation (not in use), 18 - Reverse jet tension in motion (in use), 19 - Support frame structure (indications by operation are separated and distinguished by diagonal lines or other lines). Patent Applicant Toru Fujii Procedural Amendment (Voluntary) To: Kazuo Wakasugi, Commissioner of the Adversary Agency May 9, 1981 Patent Application 2゜ Title of the Invention 3, Relationship with the Amended Person Case Patent Applicant's Application and Specification 5, Contents of correction

Claims (1)

[Claims] For direction control of a jet aircraft with a tailless structure, use of the jet nozzle flow and ambient waves; Directional control system with one-stage and two-stage combination type; (2) Directional control system with nozzle direction movable at flexible injection port; Heat-resistant materials used above (carbon fiber, 4-ceramics, titanium, etc.) Replacement method as soon as possible, taking safety into account.