GB2166698A - Vehicle simulator - Google Patents

Abstract

A vehicle simulator comprises a body (10) mounted so that it can tilt on a support (11). The support comprises a water tank (12) surmounted by a landing platform (13) on which is secured a support guide (14), and an upright support column (16) secured to a frame (17) mounted on floats (18). The column (16) is journalled in the guide (14) allowing it to slide up and down. Two cockpits (22 and 23) are provided for accommodating joyriders. The body (10) is manoeuvrable on the support by transferring water to and from water tanks (25, 26) mounted within the body, and using tip tanks (40, 41) (Fig 2). <IMAGE>

Description

SPECIFICATION Vehicle simulator This invention relates to vehicle simulators. It relates particularly, although not exclusively, to aeroplane simulators of sufficient size to accommodate an operator.

The invention provides a vehicle simulator having a support, a simulated vehicle body and means to mount the body movably on the support so that it can tilt on the support, the body comprising a control location for accommodating an operator, at least one liquid tank, and control means operable by the operator from the control location to transfer liquid to or from the or each tank so as to shift the centre of gravity of the body thereby causing it to tilt on the support.

The body preferably comprises a pair of liquid tanks arranged generally on opposite sides of the mounting means and connected together by a liquid conduit, the control means being operable to transfer liquid between the tanks along the conduit.

The body may comprise a further liquid tank positioned so that transfer of liquid thereto or therefrom causes the body to tilt in a different direction to that in which the body is caused to tilt by the transfer of liquid to or from the said one tank.

There may similarly be a pair of further liquid tanks arranged generally on opposite sides of the mounting means and connected together by a liquid conduit, the control means being operable to transfer liquid between the further tanks along the conduit.

Where there are two pairs of tanks as above, they may be arranged respectively to cause tilting of the body in two generally perpendicular planes.

The control means may comprise a liquid pump.

Alternatively or additionally, the control means may comprise an air pump, air being arranged to act on the liquid in the or each tank to cause the said transfer. Positive or negative air pressure may be used.

The body may be mounted so as to permit rotation thereof about a generally upright axis, the body comprising means operable by the operator from the control location to cause rotation of the body about the said axis. In this case, the support preferably comprises a generally upright shaft defining said axis, the rotation causing means acting to rotate the body about the shaft.

Optionally, the support may comprise first and second portions of which the second is raisable relative to the first, the body being mounted on the second portion.

An embodiment of the invention will now be described, by way of example, with reference to the accompanying drawings, in which: Figure 1 is a diagrammatic sectional side elevation of an aeroplane simulator embodying the invention; Figure 2 is a diagrammatic sectional front elevation of the aircraft body of the simulator of Figure 1; Figure 3 is a perspective diagrammatic view of the control system of the embodiment; Figure 4 shows four alternative control systems at (i) - (iv), the control system of Figure 2 being shown at (v); Figure 5 shows part of the control system of Figure 2 in five different states and another part in a static state; Figure 6 is a partial side elevation in section, showing the mechanism for turning the aircraft body about a generally upright axis; and Figure 7 is a perspective view of the turning mechanism of Figure 6.

An aeroplane simulator for a museum, leisure ground or the like comprises a model aeroplane body 10 mounted so that it can tilt on a support generally indicated 11. The support 11 is in two portions, a first portion comprising a water tank 12 surmounted by a landing platform 13 on which is secured a support guide 14, and a second portion comprising an upright support column 16 secured to a frame 17 mounted on floats 18. The column or shaft 16 is journalled in the guide 14 allowing it to slide vertically therein and thus the second portion is raisable and lowerable relative to the first portion by raising or lowering the water level in the tank 12. Alternatively, the floats couid be raised or lowered by forcing water into or out of the floats thus altering the water displacement.The body is formed with two "cockpits" 22 and 23 adapted to accommodate a youth and a child, the rear cockpit 23 being the control cockpit.

The body 10 is formed with an internal recess chamber 20 which is generally conical. This chamber can be seen in Figure 6. The body is mounted on the column 16 by means of a ball joint 21 so as to allow "universal" movement of the body 10 relative to the support 11 within the constraints of the chamber 20. The centre of gravity of the body is below the joint 21 so as to provide a "righting" force if the body is tilted.

The aeroplane body 10 is manouevred on the support by transferring water to and from water tanks mounted at suitable locations in the body as will be described hereinafter.

A nose tank 25 and a tall tank 26 are connected together as a pair by a conduit 27, the tanks 25 and 26 being located of course on opposite sides of the ball joint 21. Compressed air is supplied to a distribution valve 30 from an air pump or reservoir (not shown) the valve 30 being controlled by a "joy stick" 31. The compressed air is supplied from the valve to the tanks 25, 26 through air pipes 32, 33.

The valve 30 also incorporates valves 34, 35 which are shown in Figure 5 away from the valve 30 for clarity. When it is desired to lower the nose of the aircraft, the joy stick 31 is moved forwardly which then closes the valve 35 to atmosphere and admits compressed air along the pipe 33 to the tail tank 26, while opening valve 34 to atmosphere thus permitting air from the nose tank 25 to escape along the pipe 32 and through the valve 34 to atmosphere. The compressed air causes water to flow from the tail tank 26 along the conduit 27 to the nose tank 25, thus shifting the centre of gravity of the body forwardly. This causes the body to tilt forwardly about its "pitch" axis through an angle depending on the amount of water transferred to the nose tank.When the desired angle of pitch is reached, the joy stick is returned to its central "neutral" position which stops the flow of compressed air and opens both valves 34 and 35 to atmosphere. If it is desired to raise the nose of the aircraft, the joy stick 31 is moved backwardly and the reverse process occurs; that is, the valve 34 is closed to atmosphere and compressed air is admitted along the pipe 32 to the nose tank 35, causing water to flow back along the conduit 27 from the nose tank 25 to the tail tank 26, air in the tail tank 26 being allowed to exhaust to atmosphere along pipe 33 and through valve 35. Thus the centre of gravity of the body is moved backwardly causing the body to tilt backwardly i.e. the nose rises and the tail falls.

The conduit 27 is fitted with a vent pipe 36 branching therefrom to prevent syphoning of water between the nose and tail tank along the conduit 27 and also to limit the amount of water that can be pumped into a lowered tank.

Figures 5(i) - (v) show the pitch control system in five different states. Figure 5(i) shows the system in a static and balanced condition with the aircraft body level. The joy stick 31 is in the "neutral" position and the valves 34 and 35 are both open to atmosphere. In Figure 5(ii) it is imagined that an outof-balance force is applied to the body causing the body to pitch forwardly. This might for example by caused by a heavier child sitting in the forward cockpit 22. In order to restore balance and return the aircraft body to the horizontal position, the joy stick 31 is moved rearwardly causing water to flow from the nose tank 25 to the tail tank 26 as explained above. In Figure 5(iii) the aircraft has been levelled about the pitch axis and the out-of-balance force has been balanced by the difference in amount of water in the nose and tail tanks.The system is thus again balanced and static with both valves 34 and 35 open to atmosphere.

To obtain a nose down attitude, the joy stick 31 is moved forwardly causing water to flow from the tail tank 26 to the nose tank 25 as shown in Figure 5(iv). The water rises up the vent pipes 36 suffi cientiy to balance the excess pressure applied to the water in the tail tank 26 by the compressed air.

Figure 5(v) shows a limiting overflow condition in which a maximum amount of water has been transferred to the tail tank 26, the compressed air supplied to the nose tank 25 being allowed to escape through the vent pipe 36 as soon as the water in the conduit 27 has cleared the entrance to the vent pipe.

It will be noted that the conduit 27 is shaped upwardly adjacent to its connections to the tanks 25 and 26. This is to prevent water at a higher level transferring from one of the tanks to the other when the joy stick 31 is in the neutral position.

A similar system is used to control movement of the aircraft body about the "roll" axis, as can be seen from Figures 2, 3 and 5(vi). A pair of wing tanks 40, 41 are mounted towards the extremities of the lower "wings" of the model aircraft body 10 and these tanks are connected by a conduit 42 having a vent pipe 43 similar to vent pipe 36. Compressed air is supplied to the wing tanks 40, 41 from the distribution valve 30 along air pipes 44, 45 respectively. The distribution valve 30 also incorporates valves 46 and 47 to atmosphere from the pipes 44, 45 and these valves 46, 47 are shown away from the distribution valve 30 in Figure 5(vi) for clarity. The conduit 42 is shaped upwardly adjacent to the wing tanks 40, 41 in order to prevent water transferrinr from one tank to the other when the joy stick is in its neutral position.

Transfer of water between the wing tanks 40, 41 is controlled by the joy stick 31 in the same way as it controls the transfer of water between the nose and tail tanks accept that the joy stick is moved to the right and left in order to roll the aircraft to the right or left as desired.

In the same manner as a real aircraft joy stick the joy stick 31 can be moved to the right or left at the same time as forwardly or rearwardly in order to accomplish both roll and pitch movements of the aircraft body simultaneously.

In order to simulate realistically the flight pattern of an aircraft, a balancing wheel 50 can be installed to operate another compressed air distribution valve 51 located in a loop pipe 52 which bypasses the central distribution valve 30. The ends of the loop pipe 52 join the air pipes 32 and 33 at Tjunc- tions 53, 54. Compressed air is supplied to the distribution valve 51 and the wheel 50 can be used to make small adjustments in the relative amounts of water in the nose and tail tanks by admitting compressed air to either of the air pipes 32, 33 while permitting air to exhaust from the other of those pipes. The wheel would be spring loaded to neutralise on release.

Owing to the unknown weights of pilot and passenger the aircraft body can only be balanced after they are aboard and the balancing wheel 50 would simulate the wheel moving the trimming tabs on the elevators of a real aircraft, allowing the aircraft to be balanced about the pitch axis in a horizontal attitude without having to move the joy stick from its neutral position. Thus the balancing wheel 50 could be used to provide the balance shown in Figure 5(iii).

An alternative "trimming" system would be to arrange for the balance wheel 50 to control transfer of water between separate balancing tanks.

In order to make the aeroplane simulator more challenging to "fly", auxiliary tanks 60, 61 can be fitted in the nose and tail of the aircraft body 10 respectively. These tanks are connected together by a pipe 62 in which there is a throttle 63 to restrict flow along the pipe. These auxiliary tanks, which are independent of the joy stick control, have two functions. Firstly, they help dampen out see-saw oscillation about the pitch axis; if the nose of the aircraft body is depressed, water would commence to transfer from the tank 61 to the tank 60 (both auxiliary tanks having vents to atmosphere) thus creating an out-of-balance force partially neutralising the effects of the righting force when the joy stick has been moved to the neutral position. The aircraft body would then have to be levelled by rearward movement of the joy stick 51.Secondly, the ready flow of water from one auxiliary tank to the other would give a tendancy for the operator to overcontrol as directly the joy stick was pushed forward for a nose down attitude, water transfer would also commence along the pipe 62 so that the nose would progressively drop through a greater angle until the joy stick was brought back to check or reverse the flow in the main tanks 25, 26. The auxiliary tanks 60, 61 would therefore result in a greater nicety of control being required for level "flight".

Figures 6 and 7 show a device for producing movement of the aircraft body about its "yaw" axis similar to the effect produced by the rudder of a real aircraft. Figure 6 shows, incidently, a different shape of aircraft body 10' in which there are still two cockpits 22' and 23' but wherein the joy stick 31' is operable from the forward cockpit 22'.

The yaw axis control gear comprises a rudder bar 70 pivotally mounted in the body 10' so that it can swivel about an upright axis (relative to the body) 71. The outer ends of the rudder bar 70 are connected to low rate springs 72, 73 by cables 74, 75 and the springs 72, 73 are in turn connected at their other ends to the ends of a chain or toothed belt 76 by cables 77, 78 respectively. The cables 77, 78 pass over pullleys 80, 81 respectively so that the chain or toothed belt 76 can engage the shaft 16 at a suitable location adjacent to the joint 21. The chain or toothed belt 76 engages teeth formed on the shaft 16.

It will be understood that when the rudder bar 70 is turned to the left (by the feet of the operator), the springs 72 will be stretched and in returning to normal length causes the aircraft body to wind itself around the support shaft 16, thus simulating a yaw. Similarly, turning the rudder bar to the right will cause the spring 73 to become tensioned and cause the aircraft body to wind itself in the opposite direction around the shaft 16. The springs 72 and 73 are interposed so as to prevent a direct mechanical "feel" between the rudder bar and the support shaft 16. Furthermore, if the rudder bar 70 is moved quickly from one lock to the other, the speed of the turn of the aircraft body will be controlled by the neutral frequency of the spring.

When the rudder bar is turned to the right or left, the aircraft body will turn relative to the shaft 16 and floats 18 but because of the resistance of the water in the tank 12 to movement of the floats, there will be a net turn of the aircraft body in the desired direction relative to the tank 12 and landing platform 13. When the aircraft body has turned through a certain angie, the end of the chain or tooth belt will engage the shaft 16 causing the body to lock with the shaft. Because of the greater momentum of the body as compared with the assembly of shaft, frame 17 and floats 18, the result will be a slow turn of the aircraft body and floats relative to the landing platform 13.

It can be seen from the above that the embodiment provides an aeroplane simulator which has a very realistic "feel" for a youthful operator, movement being controlled about the pitch, roll and yaw axes together with a trimming adjustment about the pitch axis.

Figures 4(i) - (iv) show four alternative control systems to the one described in Figures 1, 2, 3 and 5, which is shown in Figure 4(v). Reference is made to the nose and tail tanks 25, 26 although these alternative systems are of course applicable also to the wing tanks 40, 41. Like elements are designated by the same reference numerals.

In Figure 4(i) the nose and tail tanks 25, 26 are sealed (as in the embodiment above) and are connected to the distribution valve 30 by pipes 32, 33 and to a reservoir tank 84 by water pipes 85, 86.

Stop-cocks 87, 88 are fitted in the pipes 85, 86 respectively. This system does not use compressed air but uses instead a water pump 89 to transfer water from the reservoir tank 84 to the nose tank or tail tank (and/or either wing tank) as appropriate. When the joy stick 31 is moved backwardly, the distribution valve 30 admits water from the water pump 89 along the pipe 33 to the tail tank while maintaining stop-cock 88 closed. Valve 35 is maintained closed to atmosphere, both valves 34 and 35 being normally closed to atmosphere. Alternative or in addition, the backward movement of the joy stick 31 opens the valve 34 to atmosphere and opens stop-cock 87. This allows water to drain from the nose tank 25 into the reservoir tank 84.

The corresponding reverse happens when the joy stick 31 is moved forwardly. When the joy stick is in the neutral position, valves 34, 35 and stopcocks 87, 88 are closed.

In Figure 4(ii) there is again a water pump 89 but no reservoir tank nor valves in the pipes 32, 33. In this system the nose and tail tanks 25, 26 are open to the atmosphere. The nose and tail tanks are connected by a conduit 27 in which there are two stop-cocks 90, 91 (which are closed when the joy stick 31 is in the neutral position) located either side of a T-junction which leads to the water pump 89. When the joy stick 31 is moved rearwardly, the stop-cock 90 is opened, while cock 91 is maintained closed, and the distribution valve 30 admits water from the water pump along the pipe 33 to the tail tank 26, the water pump 89 draining water from the nose tank 25. Thus water is transferred from the nose tank to the tail tank and the nose of the aircraft body rises. When the joy stick 31 is moved forwardly, the cock 90 closes and the cock 91 opens, the water pump 89 then pumping water from the tail tank through the cock 91 and along the pipe 32 to the nose tank 25.

The system of Figures 4(iii) and (iv) use compressed air to transfer water between the tanks 25, 26 in a similar manner to the embodiment of Figures 1, 2, 3, 4(v) and 5. In Figures 4(iii) the conduit 27 connecting the nose and tail tanks is straight and has an intermediate stop-cock 92 which is closed when the joy stick 31 is in the neutral position. When the joy stick 31 is moved rearwardly, the cock 92 opens, the valve 34 closes to atmosphere (valves 34 and 35 being open to atmosphere when the joy stick is in the neutral position) and the distribution valve 30 admits compressed air to the nose tank 25 along the pipe 32 thus causing flow of water from the nose tank to the tail tank.

The system of Figure 4(iv) is similar except that there is not stop-cock in the link pipe 27 and the valves 34 and 35 are closed to atmosphere when the joy-stick 31 is in the neutral position so as to restrict flow of water between the nose and tail tanks when the joy stick is in the neutral position.

In this last system, the conduit 27 may optionally be shaped upwardly adjacent to the nose and tail tanks in the same way as in Figure 4(v).

The simulator described above may be used as a toy for amusement purposes or may be used for training pilots.

Claims (11)

1. A vehicle simulator having a support, a simulated vehicle body and means to mount the body movably on the support so that it can tilt on the support, the body comprising a control location for accommodating an operator, at least one liquid tank, and control means operable by the operator from the control location to transfer liquid to or from the or each tank so as to shift the centre of gravity of the body thereby causing it to tilt on the support.

2. A simulator as claimed in Claim 1 wherein the body comprises a pair of liquid tanks arranged generally on opposite sides of the mounting means and connected together by a liquid conduit, the control means being operable to transfer liquid between the tanks along the conduit.

3. A simulator as claimed in either Claim 1 or Claim 2 wherein the body comprises a further liquid tank positioned so that transfer of liquid thereto or therefrom causes the body to tilt in a different direction to that in which the body is caused to tilt by the transfer of liquid to or from the said one tank.

4. A simulator as claimed in Claim 3 wherein the body comprises a pair of further liquid tanks arranged generally on opposite sides of the mounting means and connected together by a liquid conduit, the control means being operable to transfer liquid between the further tanks along the conduit.

5. A simulator as claimed in Claim 4 with dependency on Claim 2 wherein the two pairs of tanks are arranged so as respectively to cause tilting of the body in two generally perpendicular planes.

6. A simulator as claimed in any preceding claim wherein the control means comprises a liquid pump.

7. A simulator as claimed in any preceding claim wherein the control means comprises an air pump, air being arranged to act on the liquid in the or each tank to cause the said transfer.

8. A simulator as claimed in any preceding claim wherein the body is mounted so as to permit rotation thereof about a generally upright axis, the body comprising means operable by the operator from the control location to cause rotation of the body about the said axis.

9. A simulator as claimed in Claim 8 wherein the support comprises a generally upright shaft defining the said axis, the rotation causing means acting to rotate the body about the shaft.

10. A simulator as claimed in any preceding claim wherein the support comprises first and second portions of which the second is raisable relative to the first, the body being mounted on the second portion.

11. A vehicle simulator substantially as hereinbefore described with reference to and as shown in Figures 1-3, 4(v) and 5-7 or those Figures as modified by any one of Figures 4(i) - 4(iv) of the accompanying drawings.